An experimental device for verifying the nonlinear viscoelastic damage constitutive relation of high-energy propellants

Abstract

The present invention discloses an experimental device for verifying the nonlinear viscoelastic damage constitutive model of high-energy propellants, which relates to the field of propellant inspection. It includes a base, on which there is an outer shell. The base is fixedly connected with a servo motor, and the output shaft of the servo motor is fixedly connected with a lead screw, which is rotatably connected to the base. The base is fixedly connected with a first sliding shaft, and symmetrically distributed sliding seats are slidably connected to the first sliding shaft. The lead screw is threadedly connected to the symmetrically distributed sliding seats. The symmetrically distributed sliding seats are both fixedly connected with fixed disks, and a clamping box is arranged on the fixed disks. The clamping box is provided with a feed inlet, and both ends of the propellant are placed in the clamping box. A pre-tightening component is arranged in the outer shell on the base, a compaction component is arranged on the base, and a leakage prevention component is arranged on the clamping box. The present invention clamps the propellant in all directions by the sand in the box, avoiding the uneven clamping force during the stretching of the propellant, resulting in relative sliding between the propellant and the fixture, and causing errors in the stretching test data of the propellant.

Description

Technical Field

[0001] The present invention relates to the field of propellant inspection, and particularly to an experimental device for verifying the non-linear viscoelastic damage constitutive of high-energy propellants. Background Art

[0002] The non-linear viscoelastic constitutive of propellants utilizes observation techniques such as μ-CT scanning and synchrotron radiation light sources to obtain the equivalent body stress and mesoscopic structural characteristics of specific particles in high-energy propellants during the tensile force loading process, and then obtains the physical images of the propagation processes of cracks, dewetting, cavities, etc. at the interfaces of propellant particles, derives the configuration force parameters under typical loads, material properties, and mesoscopic defect conditions, and characterizes the damage degree of the material.

[0003] When the existing device stretches the propellant, due to the limitation of the propellant shape, the contact surfaces of the fixture for clamping the propellant are scarce, and the clamping force of the propellant during stretching is uneven, resulting in the propellant being extremely likely to have relative sliding with the fixture, causing the data detected during the stretching of the propellant to be inaccurate. Moreover, the existing fixtures are all hard clamping, and the propellant will have a retraction deformation during stretching, resulting in the problem that the propellant is inclined during stretching, causing the propellant to be stretched obliquely and making the detected data have errors. Summary of the Invention

[0004] In order to overcome the disadvantages of uneven clamping of the propellant by the existing fixtures and hard clamping of the fixtures, the present invention provides an experimental device for verifying the non-linear viscoelastic damage constitutive of high-energy propellants to solve the above problems.

[0005] The technical solution of the present invention is: an experimental device for verifying the non-linear viscoelastic damage constitutive of high-energy propellants, including a base, the base is provided with a housing, the housing is fixedly connected with a pressure gauge and a thermometer, the base is fixedly connected with a servo motor inside the housing, the output shaft of the servo motor is fixedly connected with a lead screw, the lead screw is rotationally connected with the base, the base is fixedly connected with a first sliding shaft, the first sliding shaft is slidably connected with symmetrically distributed sliding seats, the lead screw is threadedly connected with the symmetrically distributed sliding seats, and the symmetrically distributed sliding seats are all fixedly connected with fixing plates. It is characterized in that: the fixing plate is provided with a clamping box, the clamping box is provided with a feeding port, both ends of the propellant are placed in the clamping box, the symmetrically distributed fixing plates are all fixedly connected with tension membranes, the base is provided with a pre-tightening assembly for pre-tightening the propellant inside the housing, the base is provided with a compaction assembly for compacting the materials inside the clamping box, and the clamping box is provided with a leak-proof assembly for preventing the leakage of the materials inside the clamping box.

[0006] Preferably, the propellant is provided with circumferentially distributed clamping holes, and the clamping holes are inverted frustum blind holes, and the clamping holes are used to increase the contact area between the propellant and the materials inside the clamping box.

[0007] Preferably, the portions from the clamping positions at both ends of the propellant to the stretching position in the middle are arranged in a stepped shape to increase the circumferential and transverse clamping forces of the material in the clamping box on the propellant.

[0008] Preferably, the intersection of the clamping positions at both ends of the propellant to the stretching position in the middle is arranged as an arc surface, and the arc surface is used to offset the tensile stress acting on the intersection of the clamping positions at both ends to the stretching position in the middle when the propellant is stretched.

[0009] Preferably, the pre-tightening assembly includes a first fixing frame, the first fixing frame is fixedly connected to the base, the first fixing frame is rotatably connected with a rotating ring, the first fixing frame is fixedly connected with symmetrically distributed fixing rings, the rotating ring and the fixing rings are slidably connected with circumferentially distributed adjusting shafts, and symmetrically distributed second sliding shafts are arranged on the circumferentially distributed adjusting shafts, and clamping blocks are fixedly connected to the symmetrically distributed second sliding shafts.

[0010] Preferably, first return springs are fixedly connected between the circumferentially distributed adjusting shafts and the adjacent symmetrically distributed clamping blocks, the rotating ring is fixedly connected with uniformly distributed limiting blocks, the first fixing frame is slidably connected with a clamping block, the clamping block is in limit cooperation with the limiting block, and a second return spring is fixedly connected between the clamping block and the first fixing frame.

[0011] Preferably, the fixed disk is threadedly connected with circumferentially distributed rotating shafts, the fixed disk is slidably connected with circumferentially distributed sliding fixing blocks, and the circumferentially distributed rotating shafts are threadedly connected with the adjacent sliding fixing blocks.

[0012] Preferably, the central axis of the fixing ring is collinear with the central axis of the circumferentially distributed sliding fixing blocks.

[0013] Preferably, the compaction assembly includes a second fixing frame, the second fixing frame is fixedly connected to the base, the second fixing frame is fixedly connected with circumferentially distributed sliding rods, the clamping box is slidably connected with circumferentially distributed pressing rods, pressing plates are fixedly connected to the circumferentially distributed pressing rods in the clamping box, circumferentially distributed connecting plates are arranged in the clamping box, the circumferentially distributed pressing plates are slidably connected with the adjacent connecting plates, and third return springs are fixedly connected between the circumferentially distributed pressing rods and the clamping box.

[0014] Preferably, the leak-proof assembly includes symmetrically distributed air bags, the air bags are fixedly connected to the clamping box, the clamping box is provided with circumferentially distributed air inlet holes, and the symmetrically distributed air bags are communicated with the inner cavity of the outer shell through the circumferentially distributed air inlet holes.

[0015] The beneficial effects are as follows: 1. By uniformly clamping the propellant with the sand in the clamping box, it is avoided that the clamping force is uneven when the propellant is stretched, resulting in relative sliding between the propellant and the fixture, and causing errors in the tensile test data of the propellant.

[0016] 2. The propellant is pre-tightened by the cooperation of the rotating ring and the fixed ring, reducing the clamping time of the propellant and improving the clamping efficiency of the propellant. At the same time, the clamping block clamps the propellant, making the central axis of the propellant collinear with the central axis of the fixed ring to ensure that the propellant is horizontally stretched.

[0017] 3. The rotating ring is limited by the cooperation of the limiting block and the clamping block, making the first return spring in a compressed state. When the propellant stretches and has a retraction deformation, the clamping block always adheres to and clamps the propellant, ensuring that the central axis of the propellant is collinear with the central axis of the fixed ring.

[0018] 4. The propellant is clamped by the cooperation of the rotating shaft and the sliding fixed block to prevent the propellant from sliding relative to the clamping box under the tensile force during the stretching of the propellant, resulting in the contact between the propellant and the inner wall of the clamping box and reducing the contact area between the propellant and the sand in the clamping box.

[0019] 5. The pressing plate is extruded by the cooperation of the pressing rod and the sliding rod, and the pressing plate extrudes the sand to prevent the propellant from having a retraction deformation during stretching, resulting in the separation of the propellant from the sand due to the retraction deformation of the propellant and causing uneven clamping force of the propellant by the sand.

[0020] 6. The gas in the outer shell enters the airbag through the circumferentially distributed air inlet holes on the clamping box, and the airbag begins to expand to seal the clamping box, preventing the sand in the clamping box from leaking during the stretching of the propellant. The leakage of the sand reduces the contact area between the propellant and the sand, resulting in uneven clamping force of the propellant during stretching. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a sectional perspective structural schematic diagram of the present invention.

[0022] Figure 2 It is a perspective structural schematic diagram of the sliding seat and the clamping box of the present invention.

[0023] Figure 3 It is a perspective structural schematic diagram of the propellant of the present invention.

[0024] Figure 4 It is a perspective structural schematic diagram of the pre-tightening assembly of the present invention.

[0025] Figure 5 It is a perspective structural schematic diagram of the limiting block and the clamping block of the present invention.

[0026] Figure 6 It is a perspective structural schematic diagram of the rotating shaft and the sliding fixed block of the present invention.

[0027] Figure 7 It is a perspective structural schematic diagram of the compaction assembly of the present invention.

[0028] Figure 8 It is a perspective structural schematic diagram of the pressing plate and the connecting plate of the present invention.

[0029] Figure 9 This is a three-dimensional structural schematic diagram of the leak-proof component of the present invention.

[0030] In the attached drawing reference numerals: 101 - base, 102 - outer shell, 103 - pressure gauge, 104 - thermometer, 105 - servo motor, 106 - lead screw, 107 - first sliding shaft, 108 - sliding seat, 109 - fixed disk, 110 - clamping box, 111 - feed inlet, 112 - propellant, 113 - clamping hole, 114 - tension film, 2 - pre-tightening component, 201 - first fixing bracket, 202 - rotating ring, 203 - fixing ring, 204 - adjusting shaft, 205 - second sliding shaft, 206 - clamping block, 207 - first return spring, 208 - limiting block, 209 - locking block, 210 - second return spring, 301 - rotating shaft, 302 - sliding fixing block, 4 - compaction component, 401 - second fixing bracket, 402 - sliding rod, 403 - pressing rod, 404 - pressing plate, 405 - connecting plate, 406 - third return spring, 5 - leak-proof component, 501 - air inlet hole, 502 - airbag. Detailed implementation manners

[0031] The present invention will be further described below with reference to the embodiments shown in the attached drawings.

[0032] Embodiment 1: An experimental device for verifying the non-linear viscoelastic damage constitutive model of high-energy propellant, as Figures 1-3As shown in the figure, it includes a base 101. The base 101 is fixedly connected to a housing 102. The housing 102 is fixedly connected to a pressure gauge 103 and a thermometer 104. Inside the housing 102, the base 101 is fixedly connected to a servo motor 105. The output shaft of the servo motor 105 is fixedly connected to a lead screw 106. The lead screw 106 is a bi-directional lead screw, and the rotational directions of the threads on both sides are opposite. The lead screw 106 is rotatably connected to the base 101. The base 101 is fixedly connected to two symmetrically distributed first sliding shafts 107. Two symmetrically distributed sliding seats 108 are slidably connected to the two symmetrically distributed first sliding shafts 107. The lead screw 106 is threadedly connected to the two symmetrically distributed sliding seats 108. Each of the two symmetrically distributed sliding seats 108 is fixedly connected to a fixed disk 109. A clamping box 110 is slidably connected to the fixed disk 109. The clamping box 110 is formed by splicing two symmetrically distributed half-boxes. The two symmetrically distributed half-boxes are respectively slidably connected to the fixed disk 109 and are connected by bolts. An inlet 111 is provided at the upper part of the clamping box 110. Both ends of a propellant 112 are placed in the two symmetrically distributed clamping boxes 110. The propellant 112 is provided with circumferentially distributed clamping holes 113, and the clamping holes 113 are inverted frustum-shaped blind holes. The clamping holes 113 are used to increase the contact area between the propellant 112 and the materials in the clamping box 110. The two ends of the propellant 112 from the clamping part to the middle stretching part are set in a stepped shape, which is used to increase the circumferential and transverse clamping forces of the materials in the clamping box 110 on the propellant 112. The intersection of the two ends of the propellant 112 from the clamping part to the middle stretching part is set as an arc surface, and the arc surface is used to offset the tensile stress acting on the intersection of the two ends of the propellant 112 from the clamping part to the middle stretching part when the propellant 112 is stretched. Tension membranes 114 are fixedly connected to the two symmetrically distributed fixed disks 109, and the clamping parts of the materials in the clamping box 110 evenly clamp the propellant 112. Inside the housing 102, the base 101 is provided with a pre-tightening assembly 2 for pre-tightening the propellant 112. The base 101 is provided with a compaction assembly 4 for compacting the materials in the clamping box 110. The clamping box 110 is provided with a leak-proof assembly 5 for preventing the leakage of the materials in the clamping box 110.

[0033] As Figure 7 and Figure 8As shown, the compaction component 4 includes a second fixing frame 401, which is composed of a support frame and a fixing ring. The support frame of the second fixing frame 401 is fixedly connected to the base 101, and four sliding rods 402 distributed circumferentially are fixedly connected to the fixing ring of the second fixing frame 401. The sliding rods 402 and the fixing ring of the second fixing frame 401 are inclined outward. Four pressing rods 403 distributed circumferentially are slidably connected to the clamping box 110. Four pressing plates 404 distributed circumferentially are fixedly connected to the pressing rods 403 inside the clamping box 110. Four connecting plates 405 distributed circumferentially are arranged inside the clamping box 110. Four pressing plates 404 distributed circumferentially are slidably connected to two adjacent connecting plates 405. Third return springs 406 are fixedly connected between the four pressing rods 403 distributed circumferentially and the clamping box 110. The sliding rods 402 cooperate with the pressing plates 404 to perform circumferential equidistant extrusion on the sand material inside the clamping box 110, preventing the propellant 112 from deforming and separating from the sand material under the tensile force during stretching, resulting in uneven clamping force of the propellant 112.

[0034] When starting to stretch the propellant 112, at this time, the staff turns on the servo motor 105. The output shaft of the servo motor 105 drives the lead screw 106 to rotate synchronously. The rotation of the lead screw 106 drives two symmetrically distributed sliding seats 108 to slide away from each other through the thread. The sliding of the two sliding seats 108 away from each other drives two symmetrically distributed fixing disks 109 and two clamping boxes 110 to slide away from each other synchronously. The sliding of the two clamping boxes 110 away from each other stretches the propellant 112. At the same time, the four pressing rods 403 distributed circumferentially slide along the adjacent sliding rods 402. The four sliding rods 402 distributed circumferentially squeeze the adjacent pressing rods 403. The four pressing rods 403 distributed circumferentially slide along the clamping box 110 under the extrusion force of the adjacent sliding rods 402. The four third return springs 406 distributed circumferentially are compressed. The four sliding rods 402 distributed circumferentially sliding along the clamping box 110 drive the adjacent pressing plates 404 to slide along the clamping box 110. The pressing plates 404 sliding along the clamping box 110 squeeze the sand material inside the clamping box 110. The sand material under the extrusion force of the pressing plates 404 makes the tension film 114 always fit the surface of the propellant 112. The sand material applies a uniform clamping force to the propellant 112 through the tension film 114. At the same time, the four pressing plates 404 distributed circumferentially slide along the two adjacent connecting plates 405, preventing the propellant 112 from undergoing retraction deformation during stretching, resulting in the separation of the propellant 112 from the sand material due to retraction deformation, and causing uneven clamping force of the propellant 112 by the sand material.

[0035] When the propellant 112 is stretched, the sand enters the circumferentially distributed clamping holes 113 of the propellant 112. The sand presses against the tension film 114 and fits against the inner wall of the clamping hole 113. At the same time, the clamping area of the sand on the propellant 112 and the clamping hole 113 increases, thereby increasing the clamping force of the sand on the propellant 112. At the same time, the clamping hole 113 is a frustum-shaped blind hole, and the sand forms a frustum structure therein. The contact area between the sand and the propellant 112 from the outside to the inside of the clamping hole 113 is smaller, that is, the clamping force of the sand on the propellant 112 gradually decreases from the outside to the inside of the clamping hole 113, avoiding the superposition of the clamping force of the sand and the tensile force received by the propellant 112 inside the propellant 112, resulting in excessive stress concentration and affecting the data detection during the stretching of the propellant 112.

[0036] When the propellant 112 is stretched, since the clamping parts at both ends of the propellant 112 to the middle stretching part are arranged in a stepped shape, the contact area between the propellant 112 and the sand is further increased, and the clamping force of the sand on the propellant 112 is increased. At the same time, the clamping force of the sand on the propellant 112 is divided into a transverse clamping force and a circumferential clamping force. The transverse clamping force further strengthens the tensile force of the sand in the clamping box 110 on the propellant 112, and the circumferential clamping force ensures that the central axis of the propellant 112 coincides with the central axis of the clamping box 110 during stretching. In this way, until the stretching of the propellant 112 is completed, then the servo motor 105 is turned off. When the propellant is stretched again, the above steps are repeated.

[0037] Example 2: On the basis of Example 1, as Figure 4 shown, the pre-tightening assembly 2 includes a first fixing frame 201. The first fixing frame 201 is fixedly connected to the base 101. The first fixing frame 201 is rotatably connected to a rotating ring 202. The rotating ring 202 is provided with four circumferentially distributed inclined grooves. The first fixing frame 201 is fixedly connected with two symmetrically distributed fixing rings 203. The fixing rings 203 are provided with four circumferentially distributed straight grooves. Four circumferentially distributed adjusting shafts 204 are respectively slidably connected between the four circumferentially distributed inclined grooves of the rotating ring 202 and the four circumferentially distributed straight grooves of the fixing rings 203. Four circumferentially distributed adjusting shafts 204 are all slidably connected with two symmetrically distributed second sliding shafts 205. Two symmetrically distributed second sliding shafts 205 are both fixedly connected with clamping blocks 206. The cooperation between the rotating ring 202 and the fixing rings 203 enables the pre-tightening clamping blocks 206 to fix the propellant 112, reducing the clamping time of the propellant 112 and improving the test efficiency. At the same time, the central axis of the propellant 112 coincides with the central axis of the fixing rings 203 to ensure that the propellant 112 is horizontally stretched.

[0038] As Figure 5As shown, a first return spring 207 is fixedly connected between each of the four circumferentially distributed adjusting shafts 204 and two adjacent symmetrically distributed clamping blocks 206. The rotating ring 202 is fixedly connected with uniformly distributed limiting blocks 208. The limiting blocks 208 are wedge-shaped structures. A clamping block 209 is slidably connected to the first fixing frame 201. The clamping block 209 has an inclined surface that cooperates with the limiting block 208. The clamping block 209 and the limiting block 208 are in limit cooperation. A second return spring 210 is fixedly connected between the clamping block 209 and the first fixing frame 201. The limiting block 208 and the clamping block 209 cooperate to limit the rotating ring 202, preventing the first return spring 207 from resetting and driving the rotating ring 202 to rotate when the propellant 112 is stretched, which may cause the propellant 112 to tilt when it deforms during stretching, resulting in inaccurate detection of stretching data.

[0039] As Figure 6 shown, four circumferentially distributed rotating shafts 301 are threadedly connected to the fixed disk 109. The fixed disk 109 is slidably connected with four circumferentially distributed sliding fixing blocks 302. The sliding fixing blocks 302 have annular surfaces that fit the propellant 112. The four circumferentially distributed rotating shafts 301 are threadedly connected to the adjacent sliding fixing blocks 302. The central axis of the fixed ring 203 is collinear with the central axes of the circumferentially distributed sliding fixing blocks 302, which is used for horizontally stretching the propellant 112. The rotating shafts 301 and the sliding fixing blocks 302 cooperate to fix the propellant 112, preventing the propellant 112 from relatively sliding in the clamping box 110 under the action of the tensile force during stretching.

[0040] When the propellant 112 needs to be stretched, the staff turns the bolts to open the clamping boxes 110 on both sides, places the clamping parts at both ends of the propellant 112 into the clamping boxes 110 on both sides respectively. At the same time, the middle part of the propellant 112 for stretching is placed in two symmetrically distributed fixing rings 203. The staff sleeved two symmetrically distributed tension membranes 114 on the clamping parts at both ends of the propellant 112, and then the staff turns the bolts to close the clamping boxes 110. After the clamping boxes 110 are closed, the staff rotates the rotating ring 202 on the first fixing frame 201. The rotation of the rotating ring 202 drives the four circumferentially distributed adjusting shafts 204 to slide synchronously along the two symmetrically distributed fixing rings 203. The sliding of the four adjusting shafts 204 along the two symmetrically distributed fixing rings 203 all drives the two symmetrically distributed second sliding shafts 205 on them to slide synchronously. The sliding of the eight second sliding shafts 205 all drives the adjacent clamping blocks 206 to slide synchronously. After the eight circumferentially distributed clamping blocks 206 slide and contact the propellant 112, at this time, the central axis of the propellant 112 is collinear with the central axes of the two symmetrically distributed fixing rings 203. Through the cooperation of the fixing ring 203 and the rotating ring 202, the clamping blocks 206 pre-tighten the propellant 112, avoiding tilting when the propellant 112 is stretched, resulting in inaccurate acquisition of the stretching data of the propellant 112. At the same time, the clamping time of the propellant 112 is reduced, and the stretching test efficiency of the propellant 112 is improved.

[0041] At the same time, the rotation of the rotating ring 202 drives the evenly distributed limiting blocks 208 on it to rotate synchronously. The rotation of the limiting blocks 208 squeezes the clamping blocks 209, and the second return spring 210 is compressed. When the eight clamping blocks 206 complete the pre-tightening of the propellant 112, then the staff continues to rotate. At this time, the four circumferentially distributed adjusting shafts 204 continue to slide synchronously along the two symmetrically distributed fixing rings 203. Since the eight circumferentially distributed clamping blocks 206 have contacted and pre-tightened the propellant 112, the eight second sliding shafts 205 slide relative to the adjacent adjusting shafts 204, and the eight circumferentially distributed first return springs 207 are compressed. When the eight circumferentially distributed first return springs 207 are compressed and accumulate elastic force, stop rotating the rotating ring 202. At this time, the second return spring 210 resets. The reset of the second return spring 210 drives the clamping block 209 to limit the limiting block 208, avoiding the rotation of the rotating ring 202 driven by the elastic force accumulated by the eight first return springs 207 when the propellant 112 is stretched, resulting in tilting of the propellant 112. At the same time, when the propellant 112 is stretched and the radius of its cross-section shrinks and deforms under the tensile force, the reset of the eight first return springs 207 drives the adjacent clamping blocks 206 to always fit the propellant 112, and fixes the propellant 112 at the central axis of the fixing ring 203 all the time, ensuring its horizontal stretching.

[0042] After the preliminary fixation of the propellant 112 is completed, at this time, the staff respectively rotate the four rotating shafts 301 circumferentially distributed on the fixed disk 109 with symmetric distribution. The eight rotating shafts 301 drive the adjacent sliding fixing blocks 302 to slide along the fixed disk 109 through threads. The eight sliding fixing blocks 302 distributed circumferentially contact the propellant 112 and clamp it, so as to prevent the propellant 112 from sliding relative to the clamping box 110 under the tensile force when the propellant 112 is stretched, resulting in the contact between the propellant 112 and the inner wall of the clamping box 110, reducing the contact area between the propellant 112 and the sand in the clamping box 110, and further making the clamping force of the sand in the clamping box 110 on the propellant 112 uneven, resulting in errors in the tensile data of the propellant 112.

[0043] Example 3: On the basis of Example 2, as Figure 9 shown, the leak-proof component 5 includes two air bags 502 with symmetric distribution. The two air bags 502 with symmetric distribution are fixedly connected to the inner wall of the clamping box 110. The clamping box 110 is provided with four air inlet holes 501 distributed circumferentially. The two air bags 502 with symmetric distribution are communicated with the inner cavity of the outer shell 102 through the adjacent air inlet holes 501. When the staff apply a pressure load to the gas in the outer shell 102, at this time, the gas enters the air bag 502 from the outer shell 102 to seal the clamping box 110, so as to prevent the sand in the clamping box 110 from leaking when the propellant 112 is stretched.

[0044] After the propellant 112 is completely fixed, the staff inject sand into the clamping box 110 through the feed port 111. When the sand fills the clamping box 110, at this time, the staff close the feed port 111, and at the same time, the staff close the outer shell 102 and apply pressure and temperature loads to the outer shell 102. When the pressure of the gas in the outer shell 102 increases, at this time, the gas in the outer shell 102 enters the air bag 502 in a loose state through the four air inlet holes 501 distributed circumferentially on the clamping box 110, and then the air bag 502 starts to expand. The expansion of the air bag 502 seals the clamping box 110, so as to prevent the sand in the clamping box 110 from leaking when the propellant 112 is stretched. The leakage of the sand reduces the contact area between the propellant 112 and the sand, and the clamping force of the propellant 112 during stretching is uneven, resulting in errors in the tensile data of the propellant 112. When the gas pressure and temperature in the outer shell 102 reach the test required standard, stop applying pressure and temperature loads to the gas in the outer shell 102, and record the test data through the pressure gauge 103 and the thermometer 104.

[0045] The technical principles of the embodiments of the present invention have been described above in conjunction with specific embodiments. These descriptions are only for explaining the principles of the embodiments of the present invention and cannot be construed in any way as limiting the scope of protection of the embodiments of the present invention. Based on the explanations herein, those skilled in the art can readily conceive of other specific embodiments of the embodiments of the present invention without creative efforts, and these embodiments will fall within the scope of protection of the embodiments of the present invention.

Claims

1. An experimental device for verifying the non-linear viscoelastic damage constitutive model of high-energy propellants, comprising a base (101), the base (101) is provided with a housing (102), the housing (102) is fixedly connected with a pressure gauge (103) and a thermometer (104), a servo motor (105) is fixedly connected inside the base (101) within the housing (102), the output shaft of the servo motor (105) is fixedly connected with a lead screw (106), the lead screw (106) is rotationally connected to the base (101), the base (101) is fixedly connected with a first sliding shaft (107), the first sliding shaft (107) is slidably connected with symmetrically distributed sliding seats (108), the lead screw (106) is threadedly connected to the symmetrically distributed sliding seats (108), the symmetrically distributed sliding seats (108) are both fixedly connected with fixing plates (109), and it is characterized in that: The fixed disk (109) is provided with a clamping box (110). The clamping box (110) is provided with a feed inlet (111). Both ends of the propellant (112) are placed inside the clamping box (110). Tension membranes (114) are fixedly connected to the symmetrically distributed fixed disks (109). The base (101) is provided with a pre-tightening assembly (2) for pre-tightening the propellant (112) inside the outer shell (102). The base (101) is provided with a compaction assembly (4) for compacting the materials inside the clamping box (110). The clamping box (110) is provided with a leak-proof assembly (5) for preventing the leakage of the materials inside the clamping box (110). The compaction assembly (4) includes a second fixing frame (401). The second fixing frame (401) is fixedly connected to the base (101). The second fixing frame (401) is fixedly connected with circumferentially distributed sliding rods (402). The clamping box (110) is slidably connected with circumferentially distributed pressing rods (403). Pressing plates (404) are fixedly connected to the circumferentially distributed pressing rods (403) inside the clamping box (110). Circumferentially distributed connecting plates (405) are arranged inside the clamping box (110). The circumferentially distributed pressing plates (404) are slidably connected with the adjacent connecting plates (405). Third return springs (406) are fixedly connected between the circumferentially distributed pressing rods (403) and the clamping box (110).

2. An experimental device for verifying the nonlinear viscoelastic damage constitutive relation of high-energy propellants according to claim 1, characterized in that: The propellant (112) is provided with circumferentially distributed clamping holes (113), and the clamping holes (113) are inverted frustum blind holes, which are used to increase the contact area between the propellant (112) and the materials inside the clamping box (110).

3. An experimental device for verifying the non-linear viscoelastic damage constitutive model of high-energy propellants according to claim 2, characterized in that: The two clamping ends to the middle stretching part of the propellant (112) are arranged in a stepped shape, which is used to increase the circumferential clamping force and the transverse clamping force of the materials inside the clamping box (110) on the propellant (112).

4. An experimental device for verifying the nonlinear viscoelastic damage constitutive relation of high-energy propellants according to claim 3, characterized in that: The intersection of the two clamping ends to the middle stretching part of the propellant (112) is arranged as an arc surface, which is used to offset the tensile stress acting on the intersection of the two clamping ends to the middle stretching part when the propellant (112) is stretched.

5. An experimental device for verifying the non-linear viscoelastic damage constitutive relation of high-energy propellants as described in claim 1, characterized in that: The pre-tightening assembly (2) includes a first fixing frame (201). The first fixing frame (201) is fixedly connected to the base (101). The first fixing frame (201) is rotatably connected with a rotating ring (202). The first fixing frame (201) is fixedly connected with symmetrically distributed fixing rings (203). Circumferentially distributed adjusting shafts (204) are slidably connected between the rotating ring (202) and the fixing rings (203). Symmetrically distributed second sliding shafts (205) are arranged on the circumferentially distributed adjusting shafts (204). Clamping blocks (206) are fixedly connected to the symmetrically distributed second sliding shafts (205).

6. An experimental device for verifying the non-linear viscoelastic damage constitutive model of high-energy propellants according to claim 5, characterized in that: First return springs (207) are fixedly connected between the circumferentially distributed adjusting shafts (204) and the adjacent symmetrically distributed clamping blocks (206). Uniformly distributed limiting blocks (208) are fixedly connected to the rotating ring (202). A clamping block (209) is slidably connected to the first fixing frame (201). The clamping block (209) is in limiting cooperation with the limiting block (208). A second return spring (210) is fixedly connected between the clamping block (209) and the first fixing frame (201).

7. An experimental device for verifying the non-linear viscoelastic damage constitutive model of high-energy propellants according to claim 1, characterized in that: The fixed disk (109) is threadedly connected with circumferentially distributed rotating shafts (301). The fixed disk (109) is slidably connected with circumferentially distributed sliding fixing blocks (302). The circumferentially distributed rotating shafts (301) are threadedly connected with adjacent sliding fixing blocks (302).

8. An experimental device for verifying the nonlinear viscoelastic damage constitutive model of high-energy propellants as claimed in claim 7, characterized in that: The central axis of the fixed ring (203) is collinear with the central axes of the circumferentially distributed sliding fixing blocks (302).

9. An experimental device for verifying the non-linear viscoelastic damage constitutive relation of high-energy propellants as described in claim 1, characterized in that: The leak-proof assembly (5) includes symmetrically distributed air bags (502). The air bags (502) are fixedly connected to the clamping box (110). The clamping box (110) is provided with circumferentially distributed air inlet holes (501). The symmetrically distributed air bags (502) communicate with the inner cavity of the outer shell (102) through the circumferentially distributed air inlet holes (501).

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