Solid rocket engine in-situ heat preservation ignition test run frame

Abstract

The invention discloses a solid rocket engine in-situ heat preservation ignition test run frame which comprises a fixing base, a movable fixing plate, a supporting assembly, a force bearing pier, a first force transmission piece, a second force transmission piece, a force measuring piece, a heat preservation bottom plate and a heat preservation cover. A solid rocket engine to be tested is movably arranged on the movable fixing plate through the two supporting assemblies, and the movable fixing plate is connected to the fixing base through the multiple plate springs. The heat preservation bottom plate is arranged on the lower side of the movable fixing plate, the heat preservation cover is buckled on the heat preservation bottom plate, cold air is conveyed into the heat preservation cover through the cold air connector, the solid rocket engine to be tested can be cooled, and when the temperature of the solid rocket engine to be tested reaches the temperature required by testing conditions, the movable door is opened, and the solid rocket engine to be tested is ignited. And the force measuring piece can obtain thrust data of the solid rocket engine. The solid rocket engine in-situ heat preservation ignition test run rack can accurately simulate the thrust test of the solid rocket engine in an ultralow-temperature working environment.

Description

Technical Field

[0001] The present application relates to the technical field of solid rocket engine testing equipment, and in particular to an in-situ heat-insulated ignition test stand for a solid rocket engine. Background Art

[0002] During ground-based ignition tests of solid rocket motors, a conventional test rig is placed in the test chamber of the test stand, with the nose of the solid rocket motor resting against a bearing block. During the test, the motor is mounted on the test rig, and sensors and thrust in-situ calibration are performed. After debugging the measurement and control system, a full system rehearsal is conducted. Once everything is normal, an ignition test is conducted.

[0003] In conventional technology, during low-temperature ignition tests of solid rocket engines, the cooling and insulation processes are typically carried out in a general-purpose insulated box in a heat preservation workshop. After cooling, the solid rocket engine is transferred to a test stand on a test bench via a dedicated production vehicle for installation, thrust calibration, measurement and control system debugging, and finally ignition. The time from removing the solid rocket engine from the insulated box to ignition can range from 45 minutes to over two hours, making it impossible to accurately simulate engine ignition in ultra-low temperature environments. Summary of the Invention

[0004] An embodiment of the present application provides an in-situ insulated ignition test stand for a solid rocket engine, which can solve the problem that conventional test stands in the prior art do not have an insulation structure, resulting in the inability to accurately simulate the ignition of the engine in an ultra-low temperature environment, and the inability to achieve the requirement of immediate ignition of the engine after it leaves the insulation state.

[0005] The technical solution is as follows:

[0006] A solid rocket engine in-situ thermal insulation ignition test frame comprises: a fixing seat, a dynamic fixing plate, a support assembly, a load-bearing pier, a first force transmission member, a second force transmission member, a force measuring member, a thermal insulation bottom plate and a thermal insulation cover.

[0007] Wherein, the fixing seat includes two first support platforms and multiple second support platforms; the dynamic fixed plate is connected to the upper side of the first support platform through multiple leaf springs, and the deformation directions of the multiple leaf springs are consistent; at least two groups of support assemblies are fixedly connected to the upper surface of the dynamic fixed plate in sequence along the deformation direction of the leaf springs, and the support assemblies are used to support the solid rocket engine to be tested, and the solid rocket engine to be tested can move relative to the two groups of support assemblies after ignition. The load-bearing pier is arranged on the side of the fixing seat close to the nose of the solid rocket engine to be tested, and is used to provide supporting force to the solid rocket engine after ignition. The first force transmission member is used to be fixedly connected to the nose of the solid rocket engine to be tested. The second force transmission member is fixedly connected to the side of the load-bearing pier facing the solid rocket engine. The force measuring member is arranged between the first force transmission member and the second force transmission member, and is used to obtain thrust data of the solid rocket engine to be tested. The insulation base is fixedly connected to the second support platform and is located on the lower side of the dynamic fixed plate; the insulation cover is detachably connected to the upper side of the insulation base, and a movable door is provided on the side wall of the insulation cover near the tail end of the rocket engine.

[0008] When the thermal insulation cover is buckled onto the thermal insulation base, the solid rocket engine to be tested is located within the space enclosed by the thermal insulation base and the thermal insulation cover. A cooling air interface is provided on the thermal insulation base and / or the thermal insulation cover. A cooling air interface is provided on the thermal insulation base and / or the thermal insulation cover.

[0009] Optionally, the support assembly includes an upper clamp and a lower clamp that are detachably connected, and the upper clamp and the lower clamp are arranged outside the solid rocket engine to be tested, and the diameter of the circle formed by the upper clamp and the lower clamp is larger than the diameter of the solid rocket engine to be tested.

[0010] Optionally, a deformation groove is provided on the side of each leaf spring facing the tail end of the solid rocket motor to be tested.

[0011] Optionally, an observation window is provided on the heat-insulating cover, and a hanging ring 903 is provided on the top of the heat-insulating cover.

[0012] Optionally, the heat-insulating cover and the heat-insulating bottom plate both include an outer wall panel, an insulation layer and an inner wall panel that are sequentially arranged from the outside to the inside.

[0013] Optionally, the outer wall panels and the inner wall panels are both made of stainless steel, and the thermal insulation layer is a composite material of polyurethane foam and superfine centrifugal glass wool.

[0014] Optionally, the thermal insulation base plate has a plurality of first through holes for the leaf springs to pass through, the first through holes corresponding one to one with the leaf springs, and an insulation tube having a coaxial axis with the first through holes is provided between the thermal insulation base plate and the first support platform; the outer surface of the solid rocket engine 13 to be tested is also provided with a strain gauge and a temperature sensor, and the thermal insulation base plate 8 is also provided with a third through hole for installing a connector.

[0015] Optionally, the side wall of the thermal insulation cover near the nose of the solid rocket engine to be tested is provided with a second through hole for the first force transmission member to pass through; the first force transmission member has a force transmission shaft on the side facing the load-bearing pier, and a flexible sealing membrane is provided between the force transmission shaft and the hole wall of the second through hole.

[0016] Optionally, a heat insulating gasket is provided between the first force transmitting member and the force measuring member.

[0017] Optionally, the solid rocket engine in-situ insulation ignition test frame also includes a movable refrigeration device, and the movable refrigeration device has a cold air output pipe, and the cold air output pipe is used to connect to the cold air interface.

[0018] The beneficial effects of the technical solutions provided in the embodiments of the present application include at least:

[0019] A solid rocket engine in-situ insulation ignition test frame includes: a fixed seat, a dynamic fixed plate, a support assembly, a load-bearing pier, a first force transmission member, a second force transmission member, a force measuring member, a thermal insulation base plate, and a thermal insulation cover. The solid rocket engine to be tested is movably mounted on the dynamic fixed plate via two sets of support assemblies. The dynamic fixed plate is connected to the fixed seat via multiple leaf springs. When the solid rocket engine to be tested is ignited, the thrust generated causes the solid rocket engine to be tested to move toward the load-bearing pier. The thermal insulation base plate is disposed below the dynamic fixed plate, and the thermal insulation cover is buckled onto the thermal insulation base plate. The solid rocket engine to be tested, the dynamic fixed plate, and the support assembly are all located in the space formed by the thermal insulation base plate and the thermal insulation cover. Cold air is supplied to the thermal insulation cover through an air conditioning interface to cool the solid rocket engine to be tested. When the temperature of the solid rocket engine to be tested reaches the temperature required by the test conditions, the movable door is opened, the solid rocket engine to be tested is ignited, and the force measuring member can obtain the thrust data of the solid rocket engine. Because the leaf spring's deformation direction aligns with the thrust direction of the solid rocket motor under test, it can support the solid rocket motor under test without restricting the forward and backward movement of the fixed rocket motor under test. Therefore, the solid rocket motor in-situ thermal insulation ignition test rig of this application can accurately simulate the thrust test of a solid rocket motor in an ultra-low temperature operating environment, thereby verifying the reliability and safety of the engine system.

[0020] Other features and advantages of the present disclosure will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0022] Figure 1 This is a three-dimensional diagram of an in-situ thermal insulation ignition test stand for a solid rocket engine provided in an embodiment of the present application;

[0023] Figure 2 yes Figure 1 A three-dimensional schematic diagram of the in-situ thermal insulation ignition test stand for the solid rocket engine with the thermal insulation cover opened;

[0024] Figure 3 This is an exploded view of an in-situ thermal insulation ignition test stand for a solid rocket engine provided in an embodiment of the present application;

[0025] Figure 4 This is a perspective view of the solid rocket engine in-situ insulation ignition test stand provided by an embodiment of the present application, and a cross-sectional view cut along the front and rear leaf springs;

[0026] Figure 5 is a three-dimensional schematic diagram of a leaf spring provided in an embodiment of the present application;

[0027] Figure 6 is an exploded schematic diagram of an engine fixing assembly provided in an embodiment of the present application;

[0028] Figure 7 It is a three-dimensional schematic diagram of the thermal insulation cover provided in an embodiment of the present application.

[0029] Description of Reference Numerals

[0030] 1-fixed seat; 101-first support platform; 102-second support platform; 2-dynamic fixed plate; 3-leaf spring; 301-deformation groove; 4-support assembly; 401-upper clamp; 402-lower clamp; 5-load-bearing pier; 6-first force transmission member; 601-force transmission shaft; 7-second force transmission member; 8-insulation bottom plate; 801-first through hole; 802-third through hole; 9-insulation cover; 901-movable door; 902-observation window; 903-lifting ring; 904-second through hole; 10-force measuring member; 11-thermal insulation tube; 12-flexible sealing membrane; 13-solid rocket engine to be tested; 14-thermal insulation gasket. DETAILED DESCRIPTION

[0031] The following describes the specific embodiments of the present disclosure in detail with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only used to illustrate and explain the present disclosure and are not intended to limit the present disclosure.

[0032] In this disclosure, unless otherwise indicated, directional terms such as "upper" and "lower" generally refer to the relative positions of the corresponding components in the direction of gravity when in use. "Inside" and "outside" refer to the relative positions of the corresponding components themselves. Furthermore, the terms "first" and "second" used in this disclosure are intended to distinguish one element from another and do not convey sequential or significant meanings. In the following description, when referring to the drawings, unless otherwise indicated, identical reference numerals in different drawings indicate identical or similar elements.

[0033] According to the embodiments of this application, reference Figures 1 to 7 As shown, a solid rocket engine in-situ insulation ignition test frame includes: a fixing seat 1, a dynamic fixing plate 2, a leaf spring 3, a support assembly 4, a load-bearing pier 5, a first force transmission member 6, a second force transmission member 7, a force measuring member 10, a thermal insulation base plate 8 and a thermal insulation cover 9.

[0034] refer to Figure 3 and Figure 4 As shown, the fixing base 1 includes two first support platforms 101 and multiple second support platforms 102;

[0035] The dynamic fixing plate 2 is connected to the upper side of the first support platform 101 through a plurality of leaf springs 3 , and the deformation directions of the plurality of leaf springs 3 are consistent.

[0036] At least two groups of support assemblies 4 are fixedly connected to the upper surface of the dynamic fixed plate 2 in sequence along the deformation direction of the leaf spring 3. The support assemblies 4 are used to support the solid rocket engine 13 to be tested, and the solid rocket engine 13 to be tested can move relative to the two groups of support assemblies 4 after ignition.

[0037] The load-bearing pier 5 is arranged on one side of the fixing seat 1 close to the nose of the solid rocket engine 13 to be tested, and is used to provide supporting force to the solid rocket engine after ignition.

[0038] refer to Figure 2 and Figure 4 As shown, a first force transmission member 6 is fixedly connected to the head end of the solid rocket motor 13 to be tested. A second force transmission member 7 is fixedly connected to the side of the load-bearing pier 5 facing the solid rocket motor. A force measuring member 10 is disposed between the first force transmission member 6 and the second force transmission member 7 to obtain thrust data of the solid rocket motor to be tested.

[0039] The heat-insulating bottom plate 8 is fixedly connected to the second support platform 102 and is located on the lower side of the movable fixed plate 2;

[0040] The thermal insulation cover 9 is detachably connected to the upper side of the thermal insulation base plate 8 , and a movable door 901 is provided on the side wall of the thermal insulation cover 9 close to the tail end of the rocket engine.

[0041] When the thermal insulation cover 9 is buckled onto the thermal insulation base plate 8, the solid rocket engine 13 to be tested is located in the space enclosed by the thermal insulation base plate 8 and the thermal insulation cover 9. A cold air interface is provided on the thermal insulation base plate 8 and / or the thermal insulation cover 9.

[0042] In the above embodiment, the solid rocket engine 13 to be tested is movably mounted on the movable fixed plate 2 via two sets of support assemblies 4. The movable fixed plate 2 is connected to the fixed seat 1 via a plurality of leaf springs 3. When the solid rocket engine 13 to be tested is ignited, the thrust generated causes the solid rocket engine 13 to move toward the bearing pier 5. The thermal insulation base plate 8 is disposed below the movable fixed plate 2, and the thermal insulation cover 9 is fastened to the thermal insulation base plate 8. The solid rocket engine 13 to be tested, the movable fixed plate 2, and the support assemblies 4 are all located within the space formed by the thermal insulation base plate 8 and the thermal insulation cover 9. Cold air is supplied to the thermal insulation cover 9 via a cold air interface to cool the solid rocket engine 13 to be tested. When the temperature of the solid rocket engine 13 to be tested reaches the required temperature under the test conditions, the movable door 901 is opened, the solid rocket engine 13 to be tested is ignited, and the force measuring member 10 can obtain thrust data of the solid rocket engine. Because the deformation direction of the leaf spring 3 aligns with the thrust direction of the solid rocket motor 13 under test, the leaf spring 3 can support the solid rocket motor 13 under test without restricting the forward and backward movement of the fixed rocket motor under test. Therefore, the solid rocket motor in-situ thermal insulation ignition test rig of the present application can accurately simulate the thrust test of a solid rocket motor in an ultra-low temperature operating environment, thereby verifying the reliability and safety of the engine system.

[0043] According to the embodiments of this application, reference Figure 6As shown, the support assembly 4 includes an upper clamp 401 and a lower clamp 402 that are detachably connected. The upper clamp 401 and the lower clamp 402 are arranged around the solid rocket engine 13 to be tested, and the diameter of the circle formed by the upper clamp 401 and the lower clamp 402 is larger than the diameter of the solid rocket engine 13 to be tested. Designing the support assembly 4 as an upper clamp 401 and a lower clamp 402 can constrain the solid rocket engine 13 to be tested and prevent the solid rocket engine from flying out in a direction deviating from the design. The solid rocket engine 13 to be tested can move within the two groups of support assemblies 4, thereby reducing the influence of the support assembly 4 on the test thrust. The upper clamp 401 and the lower clamp 402 can be connected with quick-release bolts to facilitate installation and disassembly.

[0044] refer to Figure 2 and Figure 4 As shown, each leaf spring 3 is provided with a deformation groove 301 on one side facing the tail end of the solid rocket motor 13 to be tested. By providing the deformation groove 301 on the leaf spring 3, the deformation capacity of the leaf spring 3 can be further improved, thereby reducing the influence of the leaf spring 3 on the test thrust.

[0045] refer to Figure 2 and Figure 4 As shown, in order to facilitate observation of the actual situation in the heat-insulating cover 9, an observation window 902 is provided on the heat-insulating cover 9. In order to facilitate lifting the heat-insulating cover 9, a lifting ring 903 is provided on the top of the heat-insulating cover 9.

[0046] According to one embodiment of the present application, a set of observation windows with a visual area of ​​400×500mm is installed on the thermal insulation cover 9, and the glass of the observation window 902 is made of multi-layer hollow glass with electric heating film, which has high light transmittance and good heat insulation effect. When the temperature of the working room is lower than the ambient temperature, the control automatically turns on the demisting function of the observation window 902. The observation window 902 can be equipped with electric heating and automatic defrosting and demisting functions, and is sealed, heat-insulated and sound-proof. Due to the large temperature difference between the inside and outside of the thermal insulation cover 9 during operation, in order to prevent condensation or frost on the surface, the glass of the observation window 902 is a four-layer heat-insulating glass with a hollow coated electric heating wire to prevent frost. Ensure that the glass surface does not condense or frost when the temperature inside the thermal insulation cover 9 is low, remains transparent, and ensures normal observation. In order to ensure that the connection between the observation window 902 and the thermal insulation cover 9 is sealed and condensation-free, a heating wire is installed between the observation window 902 and the thermal insulation cover 9 to ensure that there is no cold leakage at the connection and no condensation on the window frame, thereby ensuring the seal between the observation window 902 and the thermal insulation cover 9.

[0047] The movable door 901 is sealed with a double-layer high and low temperature resistant silicone rubber sealing strip; a sealing strip is installed at the bottom of the door, and the bottom is sealed by a lifting hinge; an anti-frost electric heating belt is installed on the inner edge of the movable door 901, and heating and defrosting are turned on according to the temperature of the studio. The sealing performance level of the movable door 901 and the observation window 902 reaches level 4 of the airtightness test. The movable door 901 is equipped with a heating wire in the door frame to prevent frost on the outside. The door airtight material used between the movable door 901 and the insulation cover 9: a double-layer silicone rubber sealing strip, which is resistant to aging and has good sealing performance. In order to prevent condensation and frost on the door frame and door edge during low temperature testing, an automatic electric defrost device is installed in the door frame, door edge and sealing strip.

[0048] The heat-insulating cover 9 and the heat-insulating bottom plate 8 each include an outer wall plate, an insulation layer and an inner wall plate arranged in sequence from the outside to the inside. The outer wall plate and the inner wall plate are both stainless steel, and the insulation layer is a composite material of polyurethane foam and superfine centrifugal glass wool.

[0049] According to one embodiment of the present application, the exterior wall panels are constructed from 4mm thick SUS304 stainless steel, CNC machined, and electrostatically sprayed on both sides of the cold-rolled steel. The surface undergoes pickling and phosphating treatments followed by electrostatic spraying. The coating is smooth and evenly colored, with no visible base, blistering, delamination, or scratches. The exterior surface is highly corrosion-resistant and finished with a baked-on finish.

[0050] The inner wall is made of 4mm stainless steel SUS304, and all seams are continuously welded to ensure long-term leakage. In order to prevent the deformation of the inner wall of the box, several anti-deformation steel and wood frames are added, and an insulation layer is set between the outer wall and the inner wall. The insulation layer can be made of polyurethane foam with the best heat preservation effect and superimposed on ultra-fine centrifugal glass wool composite insulation layer with a thickness of 120mm. Flame retardant grade B2. The outer protection adopts non-transparent insulation material K≤0.5W / (m 2 K); the foaming density is not less than 45kg / m3; the protective layer has good thermal insulation and heat insulation properties.

[0051] The insulation base plate 8 is a double-layer austenitic stainless steel plate sandwich structure, the inner wall is coated with highly reflective aluminum foil, and the inner layer is poured with hard polyurethane foam material to form a composite insulation body, which reduces the heat leakage rate from 20W / m2 to below 10W / m2, and has special insulation performance. Stainless steel plates are laid on the insulation base plate 8 and welded as a whole, which can bear a load of ≤500kg / m2 (uniform load) and meet the strength requirements after loading the test piece.

[0052] refer to Figure 2 and Figure 4As shown, the insulating base plate 8 has a plurality of first through-holes 801 for the leaf springs 3 to pass through, each of the first through-holes 801 corresponding to the leaf springs 3. An insulating tube 11 is disposed between the insulating base plate 8 and the first support platform 101, sharing a central axis with the first through-holes 801. The upper end of the insulating tube 11 is sealed to the insulating base plate 8, and the lower end is sealed to the first support platform 101. The outer surface of the solid rocket engine 13 to be tested may also be provided with strain gauges and temperature sensors. The insulating base plate 8 is also provided with a third through-hole 802 for mounting a connector. This design facilitates testing of the deformation and temperature parameters of the solid rocket engine.

[0053] refer to Figure 2 and Figure 4 As shown, the side wall of the thermal shield 9 near the nose of the solid rocket engine is provided with a second through-hole 904 for the first force transmission member 6 to pass through. The first force transmission member 6 has a force transmission shaft 601 on the side facing the support pier 5. A flexible sealing membrane 12 is provided between the force transmission shaft 601 and the wall of the second through-hole 904. The flexible sealing membrane 12 can be made of silicone or rubber, allowing the force transmission shaft 601 to move forward and backward while also ensuring a seal between the force transmission shaft 601 and the thermal shield 9.

[0054] refer to Figure 2 and Figure 4 As shown, a heat insulating gasket 14 is provided between the first force transmitting member 6 and the force measuring member 10. In other embodiments, heat transfer can be reduced by designing a thermally insulating thermal structure.

[0055] According to an embodiment of the present application, the solid rocket engine in-situ thermal insulation ignition test frame further includes a movable refrigeration unit having a cold air output pipe, which is connected to the cold air interface. When the temperature inside the thermal insulation cover 9 needs to be lowered, the movable refrigeration unit is placed close to the solid rocket engine in-situ thermal insulation ignition test frame and the cold air output pipe is connected to the cold air interface. After the temperature inside the thermal insulation cover 9 reaches the required experimental temperature, the cold air output pipe is unplugged and the movable refrigeration unit is removed.

[0056] refer to Figures 1 to 7 As shown, the working principle of the solid rocket engine in-situ insulation ignition test stand of this application is explained below in combination with specific experimental steps:

[0057] Step 1: Use a crane to lift and remove the insulation cover, open the upper clamp in the support assembly, place the solid rocket engine to be tested on the lower clamp, and lock the upper and lower clamps;

[0058] Step 2: Use a crane to lift the thermal insulation cover above the solid rocket engine to be tested, place the thermal insulation cover on the thermal insulation base plate, adjust the position of the thermal insulation cover so that the force transmission shaft of the first force transmission member passes through the second through-hole, install the thermal insulation gasket and the force measuring member between the force transmission shaft and the second force transmission member, ensure that the first through-hole and the second through-hole are well sealed, close the movable door, and then lock the thermal insulation cover and the thermal insulation base plate;

[0059] Step 3: Move the mobile refrigeration device to the vicinity of the fixed base, connect the cold air delivery pipe and the cold air interface, start the mobile refrigeration device, allow the cold air to enter the insulation cover, and wait until the temperature inside the insulation cover reaches the set temperature. Then, remove the cold air delivery pipe and move the mobile refrigeration device away.

[0060] Step 4: Open the movable door, control the ignition of the solid rocket motor to be tested, and record the thrust value recorded by the force measuring piece;

[0061] Step 5: After the solid rocket engine has finished burning, unlock the thermal insulation cover and the thermal insulation base plate, use a crane to lift the thermal insulation cover, open the upper and lower clamps, remove the tested solid rocket engine, and the test is completed.

[0062] The preferred embodiments of the present disclosure are described in detail above in conjunction with the accompanying drawings. However, the present disclosure is not limited to the specific details of the above embodiments. Within the technical concept of the present disclosure, various simple modifications can be made to the technical solutions of the present disclosure, and these simple modifications all fall within the scope of protection of the present disclosure.

[0063] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, the present disclosure will not further describe various possible combinations.

[0064] In addition, the various embodiments of the present disclosure may be arbitrarily combined, and as long as they do not violate the concept of the present disclosure, they should also be regarded as the contents disclosed by the present disclosure.

Claims

1. A solid rocket engine in-situ insulation ignition test stand, characterized in that: include: A fixed seat (1) comprising two first support platforms (101) and a plurality of second support platforms (102); A dynamic fixed plate (2), the dynamic fixed plate (2) being connected to the upper side of the first support platform (101) via a plurality of leaf springs (3), the deformation directions of the plurality of leaf springs (3) being consistent; At least two groups of support assemblies (4) are fixedly connected to the upper surface of the movable fixed plate (2) in sequence along the deformation direction of the leaf spring (3), the support assemblies (4) are used to support the solid rocket engine (13) to be tested, and the solid rocket engine (13) to be tested can move relative to the two groups of support assemblies (4) after ignition; A load-bearing pier (5) is arranged on one side of the fixing seat (1) close to the head of the solid rocket engine (13) to be tested; A first force transmission member (6) is used for being fixedly connected to the head end of the solid rocket motor (13) to be tested; A second force transmission member (7) is fixedly connected to a side of the force-bearing pier (5) facing the solid rocket engine; A force measuring member (10) is provided between the first force transmitting member (6) and the second force transmitting member (7) and is used to obtain thrust data of the solid rocket engine (13) to be tested; A heat-insulating bottom plate (8) is fixedly connected to the second support platform (102) and is located on the lower side of the movable fixed plate (2); and a heat-insulating cover (9) detachably connected to the upper side of the heat-insulating bottom plate (8), wherein a movable door (901) is provided on a side wall of the heat-insulating cover (9) close to the tail end of the rocket engine; Wherein, when the thermal insulation cover (9) is buckled on the thermal insulation base plate (8), the solid rocket engine (13) to be tested is located in a space enclosed by the thermal insulation base plate (8) and the thermal insulation cover (9); A cold air interface is provided on the heat-insulating bottom plate (8) and / or the heat-insulating cover (9).

2. The solid rocket engine in-situ insulation ignition test stand according to claim 1, characterized in that: The support assembly (4) comprises an upper hoop (401) and a lower hoop (402) that are detachably connected, the upper hoop (401) and the lower hoop (402) being arranged outside the solid rocket engine (13) to be tested, and the diameter of the circle formed by the upper hoop (401) and the lower hoop (402) is greater than the diameter of the solid rocket engine (13) to be tested.

3. The solid rocket engine in-situ heat preservation ignition test stand according to claim 1, characterized in that: A deformation groove (301) is provided on one side of each leaf spring (3) facing the tail end of the solid rocket motor (13) to be tested.

4. The solid rocket engine in-situ insulation ignition test stand according to claim 1, characterized in that: The heat-insulating cover (9) is provided with an observation window (902), and the top of the heat-insulating cover (9) is provided with a hanging ring (903).

5. The solid rocket engine in-situ insulation ignition test stand according to claim 1, characterized in that: The heat-insulating cover (9) and the heat-insulating bottom plate (8) both comprise an outer wall plate, a heat-insulating layer and an inner wall plate which are sequentially arranged from the outside to the inside.

6. The solid rocket engine in-situ heat preservation ignition test stand according to claim 5, characterized in that: The outer wall panels and the inner wall panels are both made of stainless steel, and the thermal insulation layer is a composite material of polyurethane foam and superfine centrifugal glass wool.

7. The solid rocket engine in-situ heat preservation ignition test stand according to claim 1, characterized in that: The heat-insulating bottom plate (8) has a plurality of first through holes (801) for the leaf springs (3) to pass through, the first through holes (801) corresponding to the leaf springs (3) one by one, and a heat-insulating cylinder (11) having a coaxial axis with the first through holes (801) is provided between the heat-insulating bottom plate (8) and the first support platform (101); The outer surface of the solid rocket engine (13) to be tested is also provided with a strain gauge and a temperature sensor, and the thermal insulation bottom plate (8) is also provided with a third through hole (802) for installing a connector.

8. The solid rocket engine in-situ insulation ignition test stand according to claim 1, characterized in that: The side wall of the heat-insulating cover (9) close to the head of the solid rocket engine (13) to be tested is provided with a second through hole (904) for the first force transmission member (6) to penetrate; The first force transmission member (6) has a force transmission shaft (601) on the side facing the load-bearing pier (5), and a flexible sealing membrane (12) is provided between the force transmission shaft (601) and the hole wall of the second through hole (904).

9. The solid rocket engine in-situ heat preservation ignition test stand according to claim 1, characterized in that: A heat-insulating gasket (14) is provided between the first force-transmitting member (6) and the force-measuring member (10).

10. The solid rocket engine in-situ heat preservation ignition test stand according to claim 1, characterized in that: The solid rocket engine in-situ insulation ignition test frame also includes a movable refrigeration device, and the movable refrigeration device has a cold air output pipe, and the cold air output pipe is used to connect the cold air interface.

Images