Rocket anti-overturning device for full-rocket modal test

Abstract

The application belongs to the technical field of automatic control, and particularly relates to a rocket anti-toppling device for full-rocket modal test, a bearing ring fixed at the bottom of a rocket, a plurality of bottom lifting devices provided with pressure sensors and connected with the bottom surface of the bearing ring for supporting the rocket, a plurality of steel wire ropes with the top connected with a tower crane mechanism and the bottom connected in a circumferential manner on the bearing ring for lifting the rocket, a plurality of tower columns arranged on the ground around the rocket, a plurality of state bands arranged in a circumferential manner around the rocket, two ends of each state band connected at the same position of the tower columns and the middle part holding the outer column surface of the rocket, a state ring arranged in an equidistant manner outside the rocket and fixed on the tower columns through a state ring support beam, and a low-rigidity spring system arranged on the steel wire rope and provided with a displacement sensor for detecting the spring deformation amount of the low-rigidity spring system. The application is used for judging and preventing rocket toppling.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of automatic control, and particularly relates to a rocket anti-toppling device for full-rocket modal test. BACKGROUND

[0002] In the full-rocket modal test, the rocket is in a vertical suspension state of "free-free", simulating the flight state of the rocket in different seconds. Because the rocket is a slender structure, the center of mass is high, the mass is large, and the rocket is in a vertical suspension state, the rocket is prone to overturning, causing damage to the rocket and affecting the test progress of the full-rocket resonance modal test and subsequent tests. The commonly used method to prevent the rocket from overturning is to directly provide a transverse tension to the rocket by using a sling. This method cannot detect the initial state of the rocket toppling in time, and it is difficult to prevent the development of the initial toppling state of the rocket. Therefore, in order to further ensure the safety and controllability of the rocket test state, it is necessary to develop an anti-toppling device specially used for full-rocket modal test. SUMMARY

[0003] In order to solve the above problems, the application provides a rocket anti-toppling device for full-rocket modal test, which comprises:

[0004] A bearing ring is fixed at the bottom of the rocket;

[0005] A plurality of bottom lifting devices are installed with pressure sensors, and the bottom lifting devices are connected with the bottom surface of the bearing ring for supporting the rocket;

[0006] A plurality of steel wires are connected with the tower crane mechanism at the top and connected circumferentially on the bearing ring at the bottom for lifting the rocket;

[0007] A plurality of tower columns are arranged on the ground around the rocket;

[0008] A plurality of state bands are arranged circumferentially around the rocket, and the two ends of each state band are connected at the same position of the tower column, and the middle part holds the outer surface of the rocket;

[0009] A state ring is arranged equidistantly outside the rocket and fixed on the tower column through a state ring support beam; wherein a low stiffness spring system is arranged on the steel wire, and a displacement sensor for detecting the spring deformation of the low stiffness spring system is arranged on the low stiffness spring system.

[0010] Preferably, a ring-shaped sponge is arranged on the inner wall surface of the state ring for reducing the damage of the rocket caused by the collision of the rocket with the state ring when the rocket tilts.

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

[0012] Preferably, when the displacement sensor's monitoring value fluctuates within a preset range when the lifting device hoists the rocket through the wire rope, it is determined that the rocket is not tilted or has no tilting trend.

[0013] Preferably, when the pressure sensor's test value is the same within an error when the lifting device hoists the rocket through the wire rope, it is determined that the rocket is not tilted or has no tilting trend.

[0014] Preferably, a tightening device is arranged on the state band, the rocket tilting direction is determined according to the test value of the pressure sensor and / or the monitoring value of the displacement sensor, and the tightening device reversely tightens the state band according to the rocket tilting direction.

[0015] Preferably, the state band has at least three.

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

[0017] The advantages of the present application include:

[0018] (1) The present application can effectively monitor the test state of the rocket in each test stage, and ensure that the rocket is in a good vertical test state in the entire test stage.

[0019] (2) The present application can effectively prevent the occurrence of the rocket tilting state.

[0020] (3) The present application can timely stop the further development of the rocket tilting state when the rocket tilting state occurs, and ensure the safety of the test rocket. BRIEF DESCRIPTION OF DRAWINGS

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

[0022] Figure 2 is a schematic diagram of a bearing system;

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

[0024] Figure 4 is a schematic diagram of state band distribution;

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

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

[0027] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below in combination with the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, and are only used to explain the present application, rather than limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0028] The rocket anti-overturning device and method for full rocket modal test of the present application will be further described in detail below in combination with the drawings and specific embodiments:

[0029] The rocket anti-overturning device for full rocket modal test described above comprises a state monitoring system and a state maintaining system; as shown in Figures 1-6

[0030] The state monitoring system mainly comprises 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 comprises a bearing ring 1, a bearing ring lug 5, a lower bearing wire rope 6, a low stiffness spring system 13, a state band 14, a state ring 8, a ring-shaped sponge 7, a state ring support beam 9, a tower column 10 and the like. The state maintaining system is mainly used to maintain the suspension state of the rocket and provide correction protection measures for the weak inclination 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. The bottom lifting device 3 and the pressure sensor 4 are four groups, which are evenly distributed on the foundation, bear the pressure applied by the bearing ring 1, and monitor the pressure applied by the bearing ring 1 to the bottom lifting device at four monitoring points.

[0033] ​The rocket is installed on the bearing ring 1 through four evenly distributed arrow feet 2, which are fixed to the bearing ring 1 by bolts. Four bearing ring lugs 5 are evenly installed on the bearing ring 1 by bolts, which are divided into left and right bearing ring lugs. The shaft holes on the left and right bearing ring lugs are installed with bearing shafts, which pass through the rope rings at the lower ends of the lower bearing steel wire ropes 6 to bear the tension of the lower bearing steel wire ropes 6. The rope rings at the upper ends of the lower bearing steel wire ropes 6 are installed on the lower hanging rings 16 of the low stiffness spring system 13, and the rope rings at the lower ends of the upper bearing steel wire ropes 11 are installed on the upper hanging rings 15 of the low stiffness spring system 13. The upper bearing steel wire ropes 11 are installed on the tower top lifting mechanism through the upper rope rings. The displacement sensor 12 is installed inside the low stiffness spring system 13 by bolts, which monitors the spring deformation of the low stiffness spring system 13 to obtain the change value of the tension of the low stiffness spring system 13, which is used to judge the suspension state of the rocket.

[0034] The state band 14 surrounds the rocket, and the two ends are fixed to the tower column of the vibration tower. There are three state bands, which are distributed as shown in the figure. The state band is installed at one-half height of the rocket, and the state band cannot be too tight, so as to affect the "free-free" state of the rocket.

[0035] The inside of the state ring 8 is pasted with a ring-shaped sponge 7, and the inside of the ring-shaped sponge is spaced apart from the rocket body by about 10 cm. The ring-shaped sponge can avoid hard contact between the rocket body and the state ring, so as to reduce the damage of the rocket body caused by possible collision. The state ring 8 is spliced by two half rings, and the splicing part is connected by bolts. The outside of the state ring 8 is connected with the state ring support beam 9 through bolts, and the other end of the state ring support beam 9 is connected with the tower column through bolts. There are three turntable ring support beams, which are evenly distributed on the outside of the state ring 8.

[0036] In an optional embodiment, a tightening device is arranged on the state band 14. According to the test value of the pressure sensor 4 and / or the monitoring value of the displacement sensor, the direction of the rocket inclination is judged, and the tightening device reversely tightens the state band 14 according to the direction of the rocket inclination, so as to correct the state of the rocket body and avoid tilting.

[0037] In the above-mentioned rocket anti-tilting device and method for full rocket modal test, the test state of the rocket is guaranteed through several points:

[0038] (1) When the rocket is in the suspension test state, the displacement sensor 12 on the low stiffness spring system 13 monitors the tension change state of the bearing steel wire rope. Under normal conditions, the monitoring value of the displacement sensor should fluctuate within a small range.

[0039] (2) When the load ring 1 is placed on the bottom lifting device 3, the test values of the four pressure sensors 4 on the bottom lifting device 3 should be the same within an error, and maintain a stable value within the error. During the process of lifting the rocket by the load 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] (3) When the rocket is in the state of being embraced by the state belt, if the rocket is slightly tilted, the state belt 14 will pull the rocket to prevent further tilting of the rocket.

[0041] (4) When the tilting of the rocket further develops, the state ring 8 at the periphery of the rocket will contact the rocket body to prevent further development of the tilting of the rocket. The rocket should be at the center of the state ring 8 in any state.

[0042] The above merely describes the specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art can easily think of changes or replacements within the technical scope disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A full-scale modal test rocket anti-rollover device, characterized by, The utility model relates to a rocket lifting device, which comprises: a bearing ring (1) fixed at the bottom of a rocket; a plurality of bottom lifting devices (3) provided with pressure sensors (4) and connected with the bottom surface of the bearing ring (1) for supporting the rocket; a plurality of steel wire ropes, the top of which is connected with a tower crane mechanism and the bottom of which is connected with the bearing ring (1) in a circumferential direction for lifting the rocket; a plurality of tower columns (10) arranged on the ground around the rocket; a plurality of state bandages (14) arranged in a circumferential direction of the rocket, the two ends of each state bandage (14) being connected with the same position of the tower columns (10) and the middle part of each state bandage (14) being arranged to cover the outer surface of the rocket; a state ring (8) arranged around the rocket in an equidistant manner and fixed on the tower columns (10) through a 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); a tightening device is arranged on the state bandage (14), the inclination 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, and the tightening device reversely tightens the state bandage (14) according to the inclination direction of the rocket; the state bandage (14) has at least three state bandages.

2. The full-vehicle modal test rocket anti-rollover device of claim 1, wherein, a ring-shaped sponge (7) is arranged on the inner wall of the state ring (8) for reducing the damage of the rocket caused by the collision between the rocket and the state ring (8) when the rocket inclines.

3. The full-scale modal test rocket anti-rollover device of claim 1, wherein, the bearing ring (1) is provided with a bearing ring ear piece (5) with a double-ear structure, and a bearing shaft is arranged on the bearing ring ear piece (5), the bearing shaft being connected with the rope ring at the bottom end of the steel wire rope.

4. The full-scale modal test rocket anti-rollover device of claim 1, wherein, when the lifting device lifts the rocket through the steel wire rope, if the monitoring value of the displacement sensor fluctuates within a preset range, it is determined that the rocket is not inclined or has no inclination trend.

5. The full-scale modal test rocket anti-rollover device of claim 1, wherein, when the lifting device lifts the rocket through the steel wire rope, if the test value of the pressure sensor (4) is the same within an error range, it is determined that the rocket is not inclined or has no inclination trend.

6. The full-scale modal test rocket anti-rollover device of claim 1, wherein, the state bandage (14) is arranged at a position one-half of the height of the rocket.

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