CN115523056B - Solid rocket engine connected by clamping ring - Google Patents
Solid rocket engine connected by clamping ring Download PDFInfo
- Publication number
- CN115523056B CN115523056B CN202211344837.9A CN202211344837A CN115523056B CN 115523056 B CN115523056 B CN 115523056B CN 202211344837 A CN202211344837 A CN 202211344837A CN 115523056 B CN115523056 B CN 115523056B
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- China
- Prior art keywords
- combustion chamber
- ring
- clamping
- groove
- snap ring
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- 239000007787 solid Substances 0.000 title claims abstract description 50
- 238000007789 sealing Methods 0.000 claims abstract description 82
- 238000002485 combustion reaction Methods 0.000 claims abstract description 79
- 238000006073 displacement reaction Methods 0.000 claims description 5
- 238000003780 insertion Methods 0.000 claims description 5
- 230000037431 insertion Effects 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000036316 preload Effects 0.000 claims 3
- 238000009434 installation Methods 0.000 abstract description 9
- 230000013011 mating Effects 0.000 description 10
- 238000001125 extrusion Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
Abstract
The application relates to the field of solid rocket engines, in particular to a solid rocket engine connected by a clamping ring, which comprises: the front seal head, the combustion chamber shell, the sealing ring and the clamping ring; the combustion chamber shell is provided with a clamping ring groove, a first matching step and a second matching step, and the radial surface of the second matching step is provided with a combustion chamber shell tooth mouth groove and a combustion chamber shell tooth mouth; the front end socket comprises: the inner end face of the extension shaft is provided with a concave front end socket tooth mouth groove and a front end socket tooth mouth; the sealing ring is sleeved on the extension shaft, the front sealing head is inserted into the combustion chamber shell, the sealing ring is compressed between the inner side surface of the front sealing head body and the radial surface of the first matching step, the tooth opening of the front sealing head is inserted into the tooth opening groove of the combustion chamber shell, and the tooth opening of the combustion chamber shell is inserted into the tooth opening groove of the front sealing head; the snap ring is provided with a zoom opening with a preset distance, and the snap ring is clamped into the snap ring groove. The application can improve the installation convenience of the fixed rocket engine and the reliability of the solid rocket engine.
Description
Technical Field
The application relates to the field of solid rocket engines, in particular to a solid rocket engine connected by a clamping ring.
Background
The solid rocket engine has simple structure, convenient maintenance and high reliability, and is widely applied to missile power systems. The combustion chamber is an important part of a solid rocket engine, provides storage and combustion sites for propellants, and is also part of a missile body structure, so that the combustion chamber has enough strength and rigidity under various conditions, has lighter structural weight, is reliably connected and sealed, and has better manufacturability. However, the parts of the combustion chamber shell, the sealing head, the spray pipe and the like need to be connected, a clamping ring can be generally adopted for connection, and sealing is also needed to be considered at the connection part of the parts.
The seal structure is generally classified into an axial seal and a radial seal. If the combustion chamber shell and the seal head are axially sealed, the seal ring is arranged in the seal groove on the end face, and the seal ring needs to extend out of the seal groove to ensure the sealing effect, so that the depth of the seal groove on the end face is shallower relative to the seal ring, and for a solid rocket engine with larger slenderness, the risk of falling off the seal ring exists in the horizontal assembly of the solid rocket engine, the risk of gas leakage caused by the installation difficulty and dislocation of the seal ring is increased, and the solid rocket engine is greatly hidden in work; and the opening part of the clamping ring is the weakest link of pressure bearing under high pressure, and the periphery of the clamping ring is not provided with a restraining part for the clamping ring, so that the risk of local extrusion of the sealing ring exists. If radial sealing is adopted between the combustion chamber shell and the seal head, because the installation of the clamping ring needs to have an axial installation clearance, and because the axial compression amount does not exist, after the clamping ring is installed, a connecting piece for eliminating the axial clearance needs to be added.
Therefore, how to improve the installation convenience of the fixed rocket engine and the reliability of the solid rocket engine is a technical problem which needs to be solved by the current technicians in the field.
Disclosure of Invention
The application provides a solid rocket engine connected by a clamping ring, which is used for improving the installation convenience of a fixed rocket engine and improving the reliability of the solid rocket engine.
In order to solve the technical problems, the application provides the following technical scheme:
a snap ring connected solid rocket engine comprising: the front seal head, the combustion chamber shell, the sealing ring and the clamping ring; the inner surface of the combustion chamber shell is provided with a clamping ring groove close to the front port, the inner surface of the combustion chamber shell sequentially protrudes towards the axis direction of the combustion chamber shell to form a first matching step and a second matching step, the radial surface of the second matching step is provided with a concave combustion chamber shell tooth mouth groove, and a combustion chamber shell tooth mouth is formed between the combustion chamber shell tooth mouth groove and the circumferential surface of the second matching step; the front end socket comprises: the front end socket comprises a front end socket body and an extension shaft protruding from the inner side surface of the front end socket body, wherein the diameter of the extension shaft is smaller than that of the front end socket body, the inner end surface of the extension shaft is provided with a concave front end socket tooth mouth groove, and a front end socket tooth mouth is formed between the front end socket tooth mouth groove and the circumferential surface of the extension shaft; the sealing ring is sleeved on the extension shaft, the front sealing head is inserted into the combustion chamber shell, the sealing ring is compressed between the inner side surface of the front sealing head body and the radial surface of the first matching step, the tooth opening of the front sealing head is inserted into the tooth opening groove of the combustion chamber shell, and the tooth opening of the combustion chamber shell is inserted into the tooth opening groove of the front sealing head; the snap ring is provided with a zoom opening with a preset distance, and is clamped into the snap ring groove to limit the axial displacement of the front seal head.
The solid rocket engine connected by the clamping ring, wherein the part, close to the front end socket body, of the circumferential surface of the extension shaft is recessed to form a preassembled sealing groove, and the sealing ring is sleeved in the preassembled sealing groove.
The snap ring attached solid rocket engine as described above wherein the depth of the pre-filled seal groove is preferably less than the width of the seal ring such that a portion of the seal ring is received into the pre-filled seal groove and another portion of the seal ring extends out of the pre-filled seal groove.
The solid rocket engine connected by the snap ring as described above, wherein it is preferable that both ends of the zoom opening of the snap ring have snap ring clamp clamping handles extending toward the axial direction of the snap ring, and one end of each snap ring clamp clamping handle, which is away from the zoom opening, has a snap ring clamp clamping hole for inserting the heads of both the jaws of the snap ring clamp.
The solid rocket engine connected by the clamping ring, wherein the extending direction of the clamping hole of the clamping ring clamp is preferably the same as the axial direction of the clamping ring.
A snap ring connected solid rocket engine as described above, wherein preferably further comprising: a sealing block; the sealing block is provided with two mounting holes penetrating through two sides, and the fixing rod penetrates through the mounting holes of the sealing block and the clamping holes of the clamping pliers of the clamping handles of the clamping pliers so as to fix the sealing block between the two clamping pliers clamping handles.
The solid rocket engine with snap ring connection as described above, wherein preferably, the sealing block comprises: an insertion section and a fixing section; the width of the inserting section is smaller than that of the fixing section, the inserting section of the sealing block is inserted into the scaling opening of the clamping ring, and the fixing section of the sealing block is provided with a mounting hole.
The snap ring connected stationary rocket engine as described above, wherein it is preferable that the thickness of the fixing section of the sealing block at the position where the mounting hole is provided is smaller than the thickness of the other positions of the fixing section of the sealing block.
The solid rocket engine connected by the clamping ring is characterized in that the mounting hole on the sealing block is preferably internally provided with internal threads, and the clamping hole of the clamping ring clamp is preferably internally provided with internal threads.
The snap ring connected solid rocket engine as described above wherein the wall thickness of the combustion chamber housing adjacent the front port preferably increases gradually from inside to outside.
The beneficial effects are that:
1. the clamping type solid rocket engine adopts the clamping type mounting clamping ring connecting structure, and the mounting convenience of the clamping ring connected solid rocket engine is improved.
2. The application adopts the pre-installed sealing groove on the extending shaft of the front sealing head, thereby avoiding the risk of the falling off of the sealing ring of the solid rocket engine connected by the large slenderness ratio clamping ring in the horizontal installation process, improving the reliability of the solid rocket engine connected by the clamping ring.
3. The application adopts the mode of the staggered lap joint of the front end enclosure and the combustion chamber shell, thereby not only improving the installation reliability of the sealing ring, but also improving the deformation resistance capability of the front end enclosure under high pressure and improving the rigidity of the solid rocket engine connected by the clamping ring.
4. According to the application, the sealing block is adopted to seal the zoom opening of the snap ring after the snap ring is installed in place, so that the local rigidity of the zoom opening of the snap ring is enhanced, the risk of extrusion of the sealing ring caused by lower local strength of the zoom opening under high pressure is avoided, and the reliability of the solid rocket engine connected with the snap ring is improved.
5. According to the application, the clamping holes of the clamping ring pliers of the clamping ring are threaded holes, so that the friction force between the clamping ring pliers and the clamping holes of the clamping ring pliers is increased, and the installation efficiency of the solid rocket engine connected by the clamping ring is improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.
FIG. 1 is a cross-sectional view of a solid rocket engine with snap ring connection provided by an embodiment of the present application;
FIG. 2 is a left side view of a solid rocket engine with snap ring connection provided by an embodiment of the present application;
fig. 3 is an enlarged view of a portion a in fig. 1;
FIG. 4 is a schematic illustration of a portion of a combustor casing provided in an embodiment of the present application;
FIG. 5 is a schematic view of a portion of a front end enclosure provided by an embodiment of the present application;
fig. 6 is an enlarged view of a portion B in fig. 2;
FIG. 7 is a schematic structural view of a snap ring according to an embodiment of the present application;
FIG. 8 is a front view of a sealing block provided by an embodiment of the present application;
Fig. 9 is a right side view of a sealing block provided by an embodiment of the present application.
110-Front end enclosure, 111-front end enclosure body, 112-extension shaft, 1121-front end enclosure tooth mouth groove, 1122-front end enclosure tooth mouth, 1123-preassembly seal groove, 120-combustion chamber shell, 121-snap ring groove, 122-combustion chamber shell tooth mouth groove, 123-combustion chamber shell tooth mouth, 130-snap ring, 131-snap ring clamp clamping handle, 1311-snap ring clamp clamping hole, 140-seal ring, 150-seal block, 151-fixed section, 1511-mounting hole, 152-insertion section, 160-fastening screw.
Detailed Description
Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the application.
Referring to fig. 1 to 2, the present application provides a solid rocket engine connected by a snap ring, comprising: the front end enclosure 110, the combustion chamber shell 120, the clamping ring 130 and the sealing ring 140, wherein the front end enclosure 110 and the combustion chamber shell 120 are all important components of the solid rocket engine connected by the clamping ring.
Referring to fig. 4, the inner surface of the combustion chamber housing 120 is provided with a snap ring groove 121 near the front port, and the snap ring groove 121 is coaxial with the combustion chamber housing to accommodate the snap ring. Optionally, the depth of the snap ring groove 121 is less than the width of the snap ring 130, thereby ensuring that a portion of the snap ring 130 is received into the snap ring groove 121, while another portion of the snap ring 130 extends out of the snap ring groove 121, such that the snap ring 130 can snap the front head 110 into the front port of the combustor casing 120. Still alternatively, the width of the snap ring 130 is 2 times the depth of the snap ring groove 121.
Inside the snap ring groove 121, the inner surface of the combustion chamber housing 120 sequentially protrudes toward the axial direction of the combustion chamber housing 120, forming a first mating step and a second mating step. Wherein, the circumferential surface of the first matching step is used for contacting with the circumferential surface of the extending shaft of the front seal head 110; the radial surface of the first mating step is for contacting the seal ring 140; the circumferential surface of the second matching step is used for contacting with the inner surface of the tooth mouth groove of the front seal head 110; the radial surface of the second matching step is provided with a concave combustion chamber shell tooth mouth groove 122 for clamping into the front end socket tooth mouth, and because the radial surface of the second matching step is provided with the combustion chamber shell tooth mouth groove 122, a combustion chamber shell tooth mouth 123 is formed between the combustion chamber shell tooth mouth groove 122 on the radial surface of the second matching step and the circumferential surface of the second matching step and is used for clamping into the front end socket tooth mouth groove. Optionally, the combustion casing tooth opening groove 122 on the radial surface of the second mating step is an annular groove, and the combustion casing tooth opening groove 122 on the radial surface of the second mating step is coaxial with the combustion casing 120.
Since the inner surface of the combustion chamber housing 120 is required to be provided with the snap ring groove 121, the first mating step and the second mating step at a position near the front port, the wall thickness of the combustion chamber housing 120 near the front port gradually increases from inside to outside, where "inside" means a direction toward the middle position of the combustion chamber housing 120, and "outside" means a direction toward the front port of the combustion chamber housing 120, so that the position of the combustion chamber housing 120 near the front port has a thicker wall thickness.
Referring to fig. 5, the front seal head 110 includes: the combustion chamber comprises a front seal head body 111 and an extension shaft 112 extending from the inner side surface of the front seal head body 111 into the combustion chamber housing 120, wherein the diameter of the extension shaft 112 is smaller than that of the front seal head body 111. Wherein, the circumferential surface of the front seal head body 111 is used for contacting with the inner surface of the combustion chamber shell 120 between the clamping ring groove 121 and the radial surface of the first matching step; the inner side surface of the front seal head body 111 is used for contacting with the seal ring 140; the part of the circumferential surface of the extension shaft 112, which is close to the front end enclosure body 111, is used for contacting with the sealing ring 140, and the part of the circumferential surface of the extension shaft 112, which is far away from the front end enclosure body 111, is used for contacting with the circumferential surface of the first matching step of the combustion chamber housing 120; the inner end surface of the extension shaft 112 has a concave front end socket tooth slot 1121 for being snapped into the combustion chamber housing tooth 122 on the second mating step of the combustion chamber housing 120, and since the inner end surface of the extension shaft 112 has a concave front end socket tooth slot 1121, a front end socket tooth 1122 is formed between the front end socket tooth slot 1121 on the extension shaft 112 and the circumferential surface of the extension shaft 112 for being snapped into the combustion chamber housing tooth slot 123 on the second mating step of the combustion chamber housing 120. Alternatively, the front head tooth slot 1121 on the inner end surface of the extension shaft 112 is an annular groove, and the front head tooth slot 1121 on the inner end surface of the extension shaft 112 is coaxial with the extension shaft 112. Still alternatively, the part of the circumferential surface of the extension shaft 112, which is close to the front seal head body 111, is concaved inwards to form the preassembly seal groove 1123, so that the seal ring 140 can be preassembled in the preassembly seal groove 1123 of the extension shaft 112 before assembly, and the seal ring 140 is ensured to be always in the preassembly seal groove 1123 in the assembly process, so that the seal ring 140 is prevented from falling off in the assembly process, and the seal ring 140 is further prevented from falling off in the assembly process because the length of the extension shaft 112 is longer than the width of the preassembly seal groove 1123. Alternatively, the depth of the pre-filled seal groove 1123 is less than the width of the seal ring 140, thereby ensuring that a portion of the seal ring 140 is received within the pre-filled seal groove 1123, and a portion of the seal ring 140 extends beyond the pre-filled seal groove 1123, ensuring that the seal ring 140 remains stable in position during assembly.
Referring to fig. 3, the seal ring 140 is sleeved on the extension shaft 112 of the front end housing 110, and after the front end housing 110 is inserted into the combustion chamber housing 120, the seal ring 140 is compressed between the inner side surface of the front end housing 111 and the radial surface of the first mating step of the combustion chamber housing 120, the front end housing tooth 1122 is inserted into the combustion chamber housing tooth groove 122, and the combustion chamber housing tooth 123 is inserted into the front end housing tooth groove 1121.
Referring to fig. 6 and 7, the snap ring 130 is provided with a predetermined distance of zoom openings. Because the snap ring 130 is provided with the zoom opening, and the radial direction of the snap ring 130 has elasticity, that is, the diameter of the snap ring 130 can be increased or reduced, when the snap ring 130 is installed in the snap ring groove 121, the pre-tightening force is applied to the zoom opening, so that the zoom opening is reduced, the diameter of the snap ring 130 is reduced, the snap ring 130 can be further placed in the snap ring groove 121 in the combustion chamber shell 120, the pre-tightening force applied to the zoom opening is eliminated, the diameter of the snap ring 130 is increased, and the snap ring 130 is tightly clamped in the snap ring groove 121, so that the axial displacement of the front seal head 110 is limited. Preferably, the material of the snap ring 130 is alloy steel with good elasticity and high elongation.
Optionally, two ends of the scaling opening of the snap ring 130 are provided with snap ring clamp clamping handles 131 extending towards the axial direction of the snap ring 130, and one end of each snap ring clamp clamping handle 131 far away from the scaling opening is provided with a snap ring clamp clamping hole 1311 so as to be inserted into the heads of two clamp mouths of the snap ring clamp, so that pretightening force can be conveniently applied to the scaling opening through the snap ring clamp and the snap ring 130 can be clamped into the snap ring groove 121. Still alternatively, the extending direction of the clamping ring clamp hole 1311 is the same as the axial direction of the clamping ring 130, so that an operator can insert the head of the jaw of the clamping ring clamp into the clamping ring clamp hole 1311. Alternatively, the clamping hole 1311 of the clamping ring pliers is internally provided with an internal thread, so that on one hand, the internal thread in the clamping hole 1311 of the clamping ring pliers can increase the friction force between the head of the pliers mouth of the clamping ring pliers and the clamping hole 1311 of the clamping ring pliers, and clamping slipping is avoided, and on the other hand, the internal thread in the clamping hole 1311 of the clamping ring pliers can be in threaded connection with the mounting hole of the sealing block through a fastening screw.
On the basis, please continue to refer to fig. 1 and 2, the solid rocket engine connected by the snap ring further comprises: a sealing block 150; referring to fig. 8 and 9, two mounting holes 1511 penetrating through both sides are provided on the sealing block 150 to pass through the mounting holes 1511 of the sealing block 150 and the clamping holes 1311 of the clamping handles 131 of the clamping pliers by fixing rods, so as to fix the sealing block 130 between the two clamping handles 131 of the clamping pliers, so as to close the zoom opening of the clamping ring 130 by the sealing block 150 after the clamping ring 130 is clamped in the clamping ring groove 121, thereby enhancing the bearing capacity of the zoom opening of the clamping ring 130. Optionally, the width of the insertion section 152 of the sealing block 150 is smaller than the width of the fixing section 151 of the sealing block 150, wherein the insertion section 152 of the sealing block 150 is inserted into the scaled opening of the snap ring 130, and the fixing section 151 of the sealing block 150 is provided with a mounting hole 1511. Still alternatively, the thickness of the fixing section 151 of the sealing block 150 at the position where the mounting hole 1511 is provided is smaller than the thickness of the other positions of the fixing section 151 of the sealing block 150. Still alternatively, the mounting hole 1511 on the sealing block 150 has internal threads therein to enable the detachable connection of the sealing block 150 with the snap ring 130 by tightening the mounting hole 1511 on the sealing block 150 and the snap ring clamp hole 1311 with the fastening screw 160.
When the solid rocket engine connected by the clamping ring is assembled, the sealing ring 140 passes through the extension shaft 112 of the front end enclosure 110 and is clamped into the preassembled sealing groove 1123; then slowly loading the front end enclosure 110 with the sealing ring 140 into the combustion chamber shell 120, wherein the front end enclosure tooth opening slot 1121 is matched with the combustion chamber shell tooth opening 123, and the front end enclosure tooth opening 1122 is matched with the combustion chamber shell tooth opening slot 122; the sealing ring 140 is compressively deformed by the compression of the front head 110 and the combustion chamber housing 120 by applying a pre-tightening force to the end surface of the front head 110. In the pre-tightening state, the operator inserts the head of the jaw of the clamping ring pliers into the clamping hole 1311 of the clamping ring pliers of the clamping ring 130, so that the scaling opening of the clamping ring 130 is reduced, the clamping ring 130 is circumferentially contracted, then the clamping ring 130 is clamped into the clamping ring groove 121 of the combustion chamber shell 120, and then the head of the jaw of the clamping ring pliers is pulled out from the clamping hole 1311 of the clamping ring pliers of the clamping ring 130, so that the scaling opening of the clamping ring 130 is increased to a natural state. The sealing block 150 is then mounted to the snap ring 130 using the fastening screw 160. Finally, the pre-tightening force applied to the end surface of the front end socket 110 is removed, and the snap ring 130 bears the axial force applied by the front end socket 110 due to the internal pressure, but the axial displacement of the snap ring 130 is limited by the snap ring groove 121, so that the axial displacement of the front end socket 110 is limited by the snap ring 130.
Under the working state of the solid rocket engine connected with the clamping ring, the front seal head 110 bears the pressure of the fuel gas in the combustion chamber shell 120, the axial force is transmitted to the clamping ring 130, the clamping ring 130 is limited by the axial direction of the clamping ring groove 121, the clamping ring 130 is subjected to shearing force, and the clamping ring 130 can resist the shearing force by selecting proper material strength and size design of the clamping ring 130, so that the use requirement is met. After the front end enclosure 110 bears the internal pressure, torque is generated, the front end enclosure tooth mouth groove 1121, the combustion chamber shell tooth mouth 123, the front end enclosure tooth mouth 1122 and the combustion chamber shell tooth mouth groove 122 can further resist deformation of the front end enclosure 110, the rigidity of the front end enclosure 110 is improved, and the reliability of the solid rocket engine connected by the clamping ring is improved. The sealing ring 140 is axially in a compressed state after installation to continuously ensure the tightness of the fuel gas in the combustion chamber shell 120, and ensure the normal and reliable operation of the solid rocket engine connected by the clamping ring. The sealing block 150 is used for enhancing the rigidity of the scaled opening of the clamping ring 130 under high pressure, avoiding the risk of local extrusion of the sealing ring 140, and ensuring the normal and reliable operation of the solid rocket engine connected by the clamping ring.
It will be evident to those skilled in the art that the application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (10)
1. A snap ring connected solid rocket engine comprising: the front seal head, the combustion chamber shell, the sealing ring and the clamping ring;
The inner surface of the combustion chamber shell is provided with a clamping ring groove close to the front port, the inner surface of the combustion chamber shell sequentially protrudes towards the axis direction of the combustion chamber shell to form a first matching step and a second matching step, the radial surface of the second matching step is provided with a concave combustion chamber shell tooth mouth groove, and a combustion chamber shell tooth mouth is formed between the combustion chamber shell tooth mouth groove and the circumferential surface of the second matching step;
the front end socket comprises: the front end socket comprises a front end socket body and an extension shaft protruding from the inner side surface of the front end socket body, wherein the diameter of the extension shaft is smaller than that of the front end socket body, the inner end surface of the extension shaft is provided with a concave front end socket tooth mouth groove, and a front end socket tooth mouth is formed between the front end socket tooth mouth groove and the circumferential surface of the extension shaft;
the sealing ring is sleeved on the extension shaft, the front sealing head is inserted into the combustion chamber shell, the sealing ring is compressed between the inner side surface of the front sealing head body and the radial surface of the first matching step, the tooth opening of the front sealing head is inserted into the tooth opening groove of the combustion chamber shell, and the tooth opening of the combustion chamber shell is inserted into the tooth opening groove of the front sealing head;
the snap ring is provided with a zoom opening with a preset distance, and is clamped into the snap ring groove to limit the axial displacement of the front seal head.
2. The solid rocket engine with snap ring connection according to claim 1, wherein the part of the circumferential surface of the extension shaft, which is close to the front end socket body, is concaved inwards to form a preassembly seal groove, and the seal ring is sleeved in the preassembly seal groove.
3. A snap ring attached solid rocket engine as recited in claim 2, wherein the depth of the pre-load seal groove is less than the width of the seal ring such that a portion of the seal ring is received within the pre-load seal groove and another portion of the seal ring extends beyond the pre-load seal groove.
4. A clasp-connected solid-rocket engine according to any one of claims 1 to 3, wherein both ends of the telescoping opening of the clasp have clasp forceps holding handles extending toward the axial direction of the clasp, and one end of each clasp forceps holding handle remote from the telescoping opening has a clasp forceps holding hole for inserting the heads of the two jaws of the clasp forceps.
5. The solid rocket engine with snap ring connection according to claim 4, wherein the extending direction of the snap ring clamp clamping hole is the same as the axial direction of the snap ring.
6. A snap ring connected solid rocket engine as recited in claim 4, further comprising: a sealing block; the sealing block is provided with two mounting holes penetrating through two sides, and the fixing rod penetrates through the mounting holes of the sealing block and the clamping holes of the clamping pliers of the clamping handles of the clamping pliers so as to fix the sealing block between the two clamping pliers clamping handles.
7. A snap ring connected solid rocket engine as recited in claim 6, wherein the sealing block comprises: an insertion section and a fixing section; the width of the inserting section is smaller than that of the fixing section, the inserting section of the sealing block is inserted into the scaling opening of the clamping ring, and the fixing section of the sealing block is provided with a mounting hole.
8. A clasp-connected solid rocket engine according to claim 7, wherein the thickness of the fixed section of the sealing block at the position where the mounting hole is provided is smaller than the thickness of the other positions of the fixed section of the sealing block.
9. A solid rocket engine according to claim 6, wherein the mounting hole on the sealing block is internally threaded, and the clamping hole of the clamping ring pliers is internally threaded.
10. A snap ring connected solid rocket engine according to any of claims 1-3, wherein the wall thickness of the combustion chamber housing adjacent the front port increases gradually from inside to outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211344837.9A CN115523056B (en) | 2022-10-31 | 2022-10-31 | Solid rocket engine connected by clamping ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211344837.9A CN115523056B (en) | 2022-10-31 | 2022-10-31 | Solid rocket engine connected by clamping ring |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115523056A CN115523056A (en) | 2022-12-27 |
| CN115523056B true CN115523056B (en) | 2024-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211344837.9A Active CN115523056B (en) | 2022-10-31 | 2022-10-31 | Solid rocket engine connected by clamping ring |
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| Country | Link |
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| CN (1) | CN115523056B (en) |
Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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