Pressurizing equipment for repairing defects of heat insulating layer of shell of solid rocket engine
By designing a pressurizing device that includes a top plate, a bottom plate, a screw, a sleeve, and a heavy-duty rectangular spring, and combining it with an industrial heating blanket for high-temperature and high-pressure repair, the problem of insufficient pressure regulation in the repair of defects in the insulation layer of solid rocket motor casing was solved, and high-quality repair results were achieved.
Patent Information
- Application Number
- CN202422456765.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-11
- Publication Date
- 2025-12-09
- Estimated Expiration
- 2034-10-11
AI Technical Summary
Existing methods for repairing defects in the insulation layer of solid rocket motor casings lack pressurization equipment, resulting in poor repair results and easy detachment, and an inability to effectively regulate the pressure at the defect site.
Design a pressurizing device comprising a top plate, a bottom plate, a screw, a sleeve, a heavy-duty rectangular spring, and a nut. By adjusting the rotation of the nut to compress the heavy-duty rectangular spring, the device applies pressure to repair defective areas and combines it with an industrial heating blanket for high-temperature and high-pressure repair.
It achieves simple and practical use of pressurization equipment and low-cost repair of insulation layer defects, with good repair quality, high bonding strength, and prevention of detachment.
Smart Images
Figure CN223644326U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to the repair technology field in the field of spaceflight, especially to a solid rocket engine shell heat insulation layer defect repair pressurizing equipment. BACKGROUND
[0002] The solid rocket engine is a kind of power equipment using solid propellant, which is widely used in rockets, missiles and space vehicles. The solid rocket engine shell is a cylindrical load-bearing component and key component of the working pressure of the engine. The heat insulation structure is an important part of the solid rocket engine shell, which mainly protects the engine shell through excellent heat insulation performance and ablation resistance.
[0003] The heat insulation structure is generally divided into front and rear heads and heat insulation layers, wherein the front and rear heads are generally made by molding process of matched die pressing. After the front and rear heads are completed, they are assembled to the gypsum core mold, and then the heat insulation material sheet is laid on the gypsum core mold according to the design pattern. After the heat insulation layer is laid, carbon fiber winding is performed on the surface, and then the winding layer is co-cured together in an oven. Due to the influence of factors such as core mold gypsum quality and worker operation during the manufacturing process of the solid rocket engine shell, defects such as local debonding, depression and excess inclusion of the heat insulation layer may occur during the manufacturing process of the shell. The above-mentioned heat insulation defects will affect the normal operation of the solid rocket engine, and need to be repaired in time and effectively. The existing repair method does not have a pressurizing equipment, and the pressure at the defect of the heat insulation layer cannot be adjusted during the repair process, so the repair effect is not good and the repaired part is prone to falling off later. UTILITY MODEL CONTENTS
[0004] The utility model aims at making up for the defects of the prior art, and provides a solid rocket engine shell heat insulation layer defect repair pressurizing equipment. The utility model designs a pressurizing equipment, and adjusts the pressure of the defect area during the repair process by using the pressurizing equipment, so that the equipment is simple and practical, heating and pressurizing are convenient, the cost is low, the repair and bonding quality is good, and the heat insulation layer defects of the shell can be repaired effectively.
[0005] The utility model is implemented by the following technical solutions:
[0006] A solid rocket engine shell heat insulation layer defect repair pressurizing equipment, comprising a top plate, a bottom plate, a screw rod, a sleeve, a heavy load rectangular spring and a nut, the top end of the screw rod is fixed to the lower surface of the top plate, the bottom end of the sleeve is fixed to the upper surface of the bottom plate, the nut is screwed on the screw rod, the sleeve and the heavy load rectangular spring are both sleeved on the outside of the screw rod, wherein the heavy load rectangular spring is located between the sleeve and the nut, and a flange supporting the heavy load rectangular spring is arranged at the top end of the sleeve.
[0007] The bottom plate and the top plate are circular arc plates matching the curvature of the inner wall of the solid rocket engine shell, and the ears are arranged at the middle positions of the upper surface of the bottom plate and the lower surface of the top plate, and the circular holes are arranged on the ears.
[0008] The top end of the screw rod and the bottom end of the sleeve are respectively provided with radial circular holes, and the top end of the screw rod and the bottom end of the sleeve are respectively connected with the ears on the top plate and the bottom plate through bolts.
[0009] The nut is cylindrical, and the threaded through hole matching the screw thread of the screw rod is arranged in the middle, and two pairs of screw blind holes are symmetrically arranged on the outer side of the nut, and the screws are arranged in the screw blind holes.
[0010] The advantages of the solid rocket engine shell heat insulation layer defect repairing and pressurizing device are that the device can realize pressurizing on the heat insulation layer defect of the shell, is simple and practical, convenient to pressurize, low in cost and good in repairing quality.
[0011] The solid rocket engine shell heat insulation layer defect repairing and pressurizing device can be used for repairing the heat insulation layer defect of various solid rocket engine shells, and when the inner diameter of the heat insulation layer of the shell is large, the length of the screw rod and the sleeve can be adjusted to realize the repairing and pressurizing on the heat insulation layer defect of the shell. BRIEF DESCRIPTION OF DRAWINGS
[0012] Figure 1 The utility model discloses a structure schematic drawing:
[0013] Figure 2 It is bottom plate schematic drawing:
[0014] Figure 3 It is nut schematic drawing:
[0015] Figure 4 It is sleeve schematic drawing:
[0016] Figure 5 It is screw rod schematic drawing: DETAILED DESCRIPTION
[0017] As Figures 1-5 shown, a solid rocket engine shell heat insulation layer defect repairing and pressurizing device, including top plate 2, bottom plate 1, screw rod 5, sleeve 4, heavy load rectangular spring 6 and nut 3, the top end of screw rod 5 is fixed in top plate 2 lower surface, the bottom end of sleeve 4 is fixed on the upper surface of bottom plate 1, the nut 3 is screwed on screw rod 5, the sleeve 4 and heavy load rectangular spring 6 are all set in the outer side of screw rod 5, wherein heavy load rectangular spring 6 is located between sleeve 4 and nut 3, and the flange for supporting heavy load rectangular spring 6 is arranged at the top end of sleeve 4.After preliminary connection, the pressurizing device is placed in the heat insulation layer defect position of the shell and fixed, and the heavy load rectangular spring 6 is compressed by rotating the nut 3 to pressurize the defect area.
[0018] The maximum compression amount of the heavy load rectangular spring 6 is 24mm; and the elastic force is 1280kg.
[0019] The bottom plate 1 and the top plate 2 are circular arc plates matching the curvature of the inner wall of the solid rocket engine shell, and the ears 7 are arranged at the middle positions of the upper surface of the bottom plate 1 and the lower surface of the top plate 2, and the circular holes are arranged on the ears 7.
[0020] The top end of the screw rod 5 and the bottom end of the sleeve 4 are respectively provided with radial circular holes, and the top end of the screw rod 5 and the bottom end of the sleeve 4 are respectively connected with the ears 7 on the top plate 2 and the bottom plate 1 through bolts.
[0021] The nut 3 is a cylindrical shape, and the threaded through hole matching the thread of the screw rod 5 is arranged in the middle, and two pairs of screw blind holes 8 are symmetrically arranged on the outer side of the nut 3, and the screws are arranged in the screw blind holes 8, so that the nut 3 is conveniently adjusted.
[0022] According to the inner diameter of the heat insulation layer of the solid rocket engine shell, the size of the pressurizing equipment is determined. When repairing the defects of the heat insulation layer of the shell, the pressurizing equipment is assembled and placed in the defect position of the heat insulation layer of the shell, and the heavy load rectangular spring 6 is compressed by rotating the nut 3, and the spring pressurizes the defect repair area through the reaction force.
[0023] When the pressurizing equipment is used, the circular arc surface of the bottom plate 1 and the top plate 2 can be changed according to the size of the inner diameter of the heat insulation layer of the shell, and when the pressurizing repair is carried out, the equipment is placed at the defect position of the heat insulation layer of the shell, the middle part of the circular arc surface of the top plate 2 is in contact with the heat insulation defect area, and the spring is compressed by adjusting the nut 3 to realize the pressurization of the heat insulation defect position.
[0024] The utility model can be used for repairing and pressurizing the defects of the heat insulation layer of various solid rocket engine shells, and has the advantages of simplicity, practicality, convenience, low cost and good quality of heat insulation defect repair.
[0025] The method for repairing the defects of the heat insulation layer of the solid rocket engine shell by using the pressurizing equipment specifically comprises the following steps:
[0026] 1) Confirming the position of the debonding defect
[0027] The ultrasonic A is used to detect and mark the defect range and the thickness of the material sheet at the defect position of the heat insulation layer of the solid rocket engine shell;
[0028] 2) Polishing
[0029] The surface of the heat insulation layer of the solid rocket engine shell is polished to be matt by using the polisher, and then cleaned;
[0030] 3) Pasting the material sheet
[0031] Cutting the raw patch according to the size of the polished defect, chamfering the raw patch, and brushing the high-temperature curing adhesive on the bonding surface of the raw patch and the defect repair surface, then bonding the raw patch to the defect;
[0032] 4) Hot pressing preparation
[0033] First, cover the raw patch surface with a non-porous release film for protection, and fix it with a blue tape. Then, evenly paste the thermocouple on the edge of the hot pressing repair area, cover the industrial heating blanket on the release film of the repair area, and cover another layer of blue film on the industrial heating blanket. Install the pressing equipment, with the top plate 2 of the pressing equipment pressing against the defect of the solid rocket engine shell thermal insulation layer, and adjust the nut 3 to make the bottom plate 1 of the pressing equipment press against the inner wall of the shell opposite to the defect of the thermal insulation layer. Then, press the defect area by rotating and compressing the heavy load rectangular spring 6 through the nut 3, and heat it using the industrial heating blanket. Adjust the compression amount of the heavy load rectangular spring 6 by adjusting the nut 3, so as to control and adjust the pressure.
[0034] 5) High-temperature and high-pressure repair
[0035] Connect the digital display temperature controller of the industrial heating blanket with the thermocouple to display the temperature rise. When the temperature of the thermocouple reaches 150±5℃ and the temperature is kept constant, turn off the power of the industrial heating blanket and let it cool down to room temperature naturally. During the heating and cooling process, the pressure remains unchanged.
[0036] 6) Detection
[0037] After curing, remove the pressing equipment and use ultrasonic A to detect the bonding quality of the repair interface.
[0038] In step 1), first visually inspect the defect area of the solid rocket engine shell thermal insulation layer, then use ultrasonic A to detect and mark the debonding position of the interface.
[0039] In step 2), clean the powder and other excess materials from the polished defect interface of the solid rocket engine shell thermal insulation layer with an air gun and a cleaning cloth, then clean the debonding interface with ethyl acetate or acetone for not less than three times, and let it dry naturally for not less than 5 minutes or use a hot air gun to dry the cleaning agent on the debonding interface.
[0040] The thickness of the raw patch is 0.1-1mm greater than the thickness of the insulation layer defect, and the chamfer width is 5-15mm.
[0041] In step 3), the high-temperature curing adhesive can be used for high-temperature curing repair of thermal insulation materials, and the repair interface is evenly brushed with a wool brush according to the requirements of the adhesive.
[0042] In step 5), the temperature of the electric heating blanket is controlled by the thermocouple.
[0043] In the step 5), the pressing device uses the specific steps as follows:
[0044] 5a) clean the surface of the pressing device of dirt and other excess materials.
[0045] 5b) initially connect the bottom plate 1, the top plate 2, the nut 3, the sleeve 4, the screw 5 and the heavy load rectangular spring 6.
[0046] 5c) place the pressing device on the defect area of the thermal insulation layer, and adjust the nut 3 to contact the arc surface of the top plate 2 with the defect repair position of the thermal insulation layer.
[0047] 5d) adjust the nut 3 to compress the heavy load rectangular spring 6 to pressurize the defect position.
[0048] 5e) remove the pressing device after the pressing of the thermal insulation defect is completed.
[0049] In the step 4), during the pressure adjustment, the rotation of the nut 3 compresses the heavy load rectangular spring 6 to generate a compression amount L1, and the heavy load rectangular spring 6 generates a compression force Fn, so that the formula: compression force Fn=spring constant K*compression amount L1 is obtained, and the pressure f acting on the repair area S is Fn, and the pressure P acting on the repair area is f / S=spring constant K*compression amount L1 / S.
[0050] Wherein, the spring constant K and the repair area are both specific constants, so the pressure f is proportional to the compression amount L1 of the heavy load rectangular spring 6, and the pressure intensity acting on the repair area can be adjusted by controlling the compression amount L1 of the heavy load rectangular spring 6 through the rotation of the nut 3.
[0051] In the step 6), after the adhesive is cured, the pressing device is removed, the non-porous isolation film for isolation and protection is removed, the ultrasonic A scanning is used to detect the repair interface, and the bonding quality of the repair interface is confirmed.
[0052] The interlayer pull-off strength and the shear strength of the thermal insulation layer after the repair of the thermal insulation layer are both greater than 2MPa, the oxyacetylene linear ablation rate is less than 0.09mm / s, and the defect is well bonded.
[0053] The preferred embodiments are only the preferred embodiments of the utility model, and it should be pointed out that, for ordinary skilled persons in the technical field, some improvements and decorations can be made without departing from the concept of the utility model, and these improvements and decorations should also be regarded as being within the protection range of the utility model.
Claims
1. A solid rocket motor case insulation defect repair pressurization apparatus, characterized by: The device comprises a top plate, a bottom plate, a screw rod, a sleeve, heavy load rectangular springs and a nut, the top end of the screw rod is fixed on the lower surface of the top plate, the bottom end of the sleeve is fixed on the upper surface of the bottom plate, the nut is screwed on the screw rod, the sleeve and the heavy load rectangular springs are both sleeved on the outside of the screw rod, wherein the heavy load rectangular springs are located between the sleeve and the nut, and a flange is arranged on the top end of the sleeve to support the heavy load rectangular springs.
2. The solid rocket motor case insulation defect repair pressurization apparatus of claim 1, wherein: The bottom plate and the top plate are both circular arc plates matching the curvature of the inner wall of the solid rocket engine shell, and an ear is arranged on the middle position of the upper surface of the bottom plate and the lower surface of the top plate, and a round hole is formed in the ear.
3. The solid rocket motor case insulation defect repair pressurization apparatus of claim 2, wherein: The top end of the screw rod and the bottom end of the sleeve are respectively provided with radial round holes, and the top end of the screw rod and the bottom end of the sleeve are respectively connected with the ears on the top plate and the bottom plate through bolts.
4. The apparatus according to claim 1, wherein the apparatus is characterized by: The nut is cylindrical, and a threaded through hole matching the screw thread of the screw rod is arranged in the middle of the nut, two pairs of screw blind holes are symmetrically arranged on the outside of the nut, and screws are installed in the screw blind holes.