CN112943482A - Integral frame of liquid rocket engine - Google Patents
Integral frame of liquid rocket engine Download PDFInfo
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- CN112943482A CN112943482A CN202110104339.6A CN202110104339A CN112943482A CN 112943482 A CN112943482 A CN 112943482A CN 202110104339 A CN202110104339 A CN 202110104339A CN 112943482 A CN112943482 A CN 112943482A
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
The invention provides an integral frame of a liquid rocket engine, which solves the problems of relatively large structural quality and outline shape of the existing engine frame in a combined welding or assembling connection mode. The frame comprises a precision measurement lens, an upper flange plate, a lower flange plate, 4 main beams, 2V-shaped side beams and 2 mounting planes which are integrally processed; the upper flange plate is provided with a plurality of first butt joint holes, wherein 2 first butt joint holes are used as reference positioning holes; the lower flange plate is coaxially arranged below the upper flange plate, a plurality of second butt holes are formed in the lower flange plate, and the lower surface of the lower flange plate is provided with a heat insulation layer and two positioning grooves which are symmetrically arranged; the two ends of each of the 4 main beams are respectively connected with the upper flange plate and the lower flange plate, the 4 main beams are uniformly distributed along the circumferential direction, the 2 mounting planes and the 2V-shaped side beams are arranged between the adjacent main beams, and the accurate measurement mirror is arranged on the outer side of the lower flange plate and used as a reference for thrust vector expression.
Description
Technical Field
The invention belongs to the field of liquid rocket engine design, relates to a frame for a liquid rocket engine, and particularly relates to an integral frame of the liquid rocket engine.
Background
The liquid rocket engine is generally arranged on a bearing structure of an rocket body structure, but is limited by the installation position of the engine, the form of a connector and the installation envelope, the liquid rocket engine and the rocket body need to be connected through a frame or a rack, the frame or the rack is a component for bearing the connection, support and transmission thrust between the engine and the rocket body, and the liquid rocket engine also needs to bear bending moment and torque when the rocket body pitches, yaws and rolls. The structural performance of the frame or frame itself therefore directly affects the reliability of the connection between the engine and the overall structure.
The traditional engine frame or frame is generally designed into a rod-type or beam-type structure, and usually adopts a combined welding or assembling connection mode, but the frame or frame structure has relatively large mass and outer contour shape, occupies a large space and has low structural utilization efficiency.
Disclosure of Invention
The invention provides an integral frame of a liquid rocket engine, which aims to solve the technical problems that the existing engine frame (or frame) adopts a combined welding or assembling connection mode, the structural mass and the outer contour shape are relatively large, and the structural utilization efficiency is low.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
the integral frame of the liquid rocket engine is characterized in that: the device comprises a precision measurement mirror, an integrally processed upper flange plate, a lower flange plate, 4 main beams, 2V-shaped side beams and 2 mounting planes;
a plurality of first butt holes are formed in the upper flange plate along the circumferential direction, wherein 2 first butt holes are used as reference positioning holes;
the lower flange plate is coaxially arranged below the upper flange plate, the inner diameter of the lower flange plate is smaller than that of the upper flange plate, the outer diameter of the lower flange plate is smaller than that of the upper flange plate, a plurality of second butt joint holes are formed in the lower flange plate along the circumferential direction, and a heat insulation layer and two symmetrically arranged positioning grooves are formed in the lower surface of the lower flange plate;
two ends of the 4 main beams are respectively connected with the upper flange plate and the lower flange plate, the 4 main beams are uniformly distributed along the circumferential direction, and the 4 main beams are respectively a first main beam, a second main beam, a third main beam and a fourth main beam which are sequentially arranged along the circumferential direction;
the 2 mounting planes are respectively a first mounting plane and a second mounting plane, the first mounting plane is arranged between the first main beam and the second main beam, and the second mounting plane is arranged between the third main beam and the fourth main beam;
the 2V-shaped side beams are respectively a first V-shaped side beam and a second V-shaped side beam, the first V-shaped side beam is arranged between the first main beam and the fourth main beam, and the second V-shaped side beam is arranged between the second main beam and the third main beam;
the precise measuring mirror is arranged on the outer side of the lower flange plate and used as a reference for thrust vector expression.
Furthermore, the plurality of first butt joint holes are 2N first butt joint holes which are uniformly distributed on the circumference, N is an integer larger than or equal to 2, and the 2 reference positioning holes are symmetrically arranged.
Furthermore, the first V-shaped side beam comprises a first supporting beam and a second supporting beam, one end of the first supporting beam and one end of the second supporting beam are intersected and connected to the upper flange, the other end of the first supporting beam is arranged at the joint of the fourth main beam and the lower flange, and the other end of the second supporting beam is arranged at the joint of the first main beam and the lower flange;
the second V-shaped side beam and the first V-shaped side beam are identical in structure, and the opening directions of the V shapes are opposite.
Further, the thermal insulation layer is made of a low-thermal-conductivity material.
Furthermore, each main beam is provided with a reinforcing rib, and the positioning groove is a U-shaped key groove.
Furthermore, the upper flange plate, the lower flange plate, the 4 main beams, the 2V-shaped side beams and the 2 mounting planes are made of titanium alloy materials.
Furthermore, grooves are formed between two adjacent first butt joint holes in the upper flange plate and between two adjacent second butt joint holes in the lower flange plate.
Further, the first installation plane and the second installation plane are both provided with installation holes.
Compared with the prior art, the invention has the advantages that:
1. the frame is integrally designed and has mechanical load resistance, the upper flange plate, the lower flange plate and the 4 main beams form a basic frame structure, the structure is simple, the weight is light, the axial length and the outline of the engine are smaller, the four main beams are used as main force bearing and transferring structures, corresponding reinforcing ribs are designed for reinforcement, and the reliability is improved; a mounting plane is designed between the adjacent main beams, so that the engine assembly is conveniently mounted; the V-shaped side beam between the adjacent main beams is beneficial to structural stability and weight reduction; and the thermal insulation layer is prepared on the lower flange plate, so that the heat conduction is reduced on the basis of ensuring the structural strength, the temperature of the upper flange can be reduced to be not more than 50 ℃, and the thermal influence of the high temperature of the thrust chamber of the rocket engine on other structural components is effectively isolated.
2. According to the invention, the lower flange plate is provided with the precise measurement mirror, so that the allowance of the upper flange plate can be corrected and processed according to the thrust line measurement result of the engine hot standard, and the precision of the thrust line can be accurately controlled.
3. The existing integral frame is generally applied to an engine with lower thrust, is not generally used as a mounting structure of other components, and does not have the function of specially blocking heat conduction and controlling heat transfer. The frame of the invention has light weight, high mechanical load resistance, simple structure and small overall envelope, the installation plane can realize the installation of other components, and the heat insulation layer on the lower surface of the lower flange plate can effectively obstruct heat conduction.
4. The upper flange plate and the lower flange plate are provided with positioning structures (a reference positioning hole and a positioning groove), so that the positioning structures can be accurately positioned, and the thrust vector position is ensured under the condition that the engine is repeatedly disassembled and assembled.
Drawings
FIG. 1 is a schematic structural view of an integral frame of a liquid rocket engine of the present invention;
wherein the reference numbers are as follows:
1-an upper flange, 11-a first butt joint hole, 2-a lower flange, 21-a second butt joint hole, 31-a first main beam, 32-a second main beam, 34-a fourth main beam, 41-a first mounting plane, 42-a second mounting plane, 43-a mounting hole, 51-a first V-shaped side beam, 511-a first support beam, 512-a second support beam, 52-a second V-shaped side beam, 6-a precision measurement mirror, 7-a reinforcing rib and 8-a groove.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
As shown in fig. 1, an integral frame of a liquid rocket engine comprises an upper flange plate 1, a lower flange plate 2, 4 main beams, 2V-shaped side beams and 2 mounting planes; the upper flange plate 1, the lower flange plate 2, 4 main beams, 2V-shaped side beams and 2 mounting planes are integrally processed to form the frame, and meanwhile, the frame has a weight reduction design, so that the frame is good in structural rigidity and simple and reliable in structure.
The lower flange plate 2 is coaxially arranged below the upper flange plate 1, the size of the lower flange plate 2 is smaller than that of the upper flange plate 1, namely the inner diameter of the lower flange plate 2 is smaller than that of the upper flange plate 1, the outer diameter of the lower flange plate 2 is smaller than that of the upper flange plate 1, two ends of 4 main beams are respectively connected with the upper flange plate 1 and the lower flange plate 2, the 4 main beams are uniformly distributed along the circumferential direction, the upper flange plate 1, the lower flange plate 2 and the 4 main beams form a variable-section cylindrical structure, the upper flange plate 1 is used for being in butt joint with the whole body, and the lower flange plate 2 is in butt joint with a rocket engine thrust chamber (an injector flange of the thrust chamber) and can be repeatedly disassembled and assembled.
The invention adopts 4 main beams as main bearing structures, and designs corresponding reinforcing ribs 7 for reinforcement; the 4 main beams are respectively a first main beam 31, a second main beam 32, a third main beam and a fourth main beam 34; the 2V-shaped side beams are respectively a first V-shaped side beam 51 and a second V-shaped side beam 52, the first V-shaped side beam 51 is arranged between the first main beam 31 and the fourth main beam 34, the second V-shaped side beam 52 is arranged between the second main beam 32 and the third main beam, and the V-shaped side beams are designed among the main beams, so that the structure stability is facilitated, and the torsional rigidity is improved.
In this embodiment, the first V-shaped side beam 51 includes a first supporting beam 511 and a second supporting beam 512, one end of the first supporting beam 511 and one end of the second supporting beam 512 intersect and are connected to the upper flange 1, the other end of the first supporting beam 511 is disposed at the connection between the fourth main beam 34 and the lower flange 2, and the other end of the second supporting beam 512 is disposed at the connection between the first main beam 31 and the lower flange 2; the second V-shaped side member 52 is opened in the opposite direction to the first V-shaped side member 51.
The 2 installation planes are a first installation plane 41 and a second installation plane 42 respectively, the first installation plane 41 and the second installation plane 42 are both provided with installation holes 43, the first installation plane 41 is arranged between the first main beam 31 and the second main beam 32, and the second installation plane 42 is arranged between the third main beam and the fourth main beam 34; and a mounting plane is designed between the main beams and is used for mounting other components of the engine.
2N uniformly distributed first butt joint holes 11 are formed in the upper flange plate 1 along the circumferential direction, N is an integer larger than or equal to 2, the precision of the symmetrically distributed 2 first butt joint holes 11 is higher than that of the rest first butt joint holes 11, the symmetrically distributed 2 first butt joint holes 11 are used as reference positioning holes, and the rest first butt joint holes 11 are used for realizing the fixation of the upper flange plate 1 and the whole body through bolts; a plurality of second butt joint holes 21 are uniformly distributed in the circumferential direction on the lower flange plate 2, and the lower flange plate 2 and the rocket engine thrust chamber are fixed through bolts. In this embodiment, the first and second connection holes 11 and 21 are equal in number and corresponding in position one to one, and are all 8 holes uniformly distributed circumferentially; grooves 8 are formed between two adjacent first butt joint holes 11 in the upper flange plate 1 and between two adjacent second butt joint holes 21 in the lower flange plate 2, and therefore the weight reduction design is achieved.
The upper flange plate 1 and the lower flange plate 2 are both provided with a positioning structure. The positioning structure on the lower flange plate 2 is used for fixing a thrust line of the thrust chamber, so that the position of the thrust line is unchanged when the engine is repeatedly installed, the positioning structure on the lower flange plate 2 is two positioning grooves symmetrically formed in the lower surface of the lower flange plate 2, correspondingly, a positioning block matched with the positioning grooves is arranged on the thrust chamber (an injector flange of the thrust chamber), and the positioning grooves on the lower flange plate 2 and the positioning block on the thrust chamber are positioned and installed, so that the accurate positioning of the lower flange plate 2 and the thrust chamber is realized. The positioning structure on the upper flange plate 1 is used for positioning the relative position of the engine reference coordinate and the hot standard test run rack reference coordinate and is used as a thrust line data reference; go up the location structure on the ring flange 1 for above-mentioned wherein symmetrical arrangement's 2 first butt joint holes 11(2 benchmark locating holes), correspondingly, be equipped with on the assembly (the rack ring flange of taking a trial run) with 2 reference columns of 2 benchmark locating hole cooperations, go up 2 benchmark locating holes on the ring flange 1 and 2 reference columns location installations on the assembly, realize going up the accurate location of ring flange 1 and the rack of taking a trial run.
In the embodiment, the upper flange plate 1 and the lower flange plate 2 both adopt weight reduction design, the diameter phi of the outer ring of the upper flange plate 1 is 200mm, the diameter phi of the inner ring is 160mm, the diameter phi of the outer ring of the lower flange plate 2 is 180mm, and the diameter phi of the inner ring is 144 mm; the main beam is 4mm in thickness and 26mm in width, T-shaped reinforcing ribs are designed for reinforcement, and the positioning grooves of the lower flange plate 2 are U-shaped key grooves and used for fixing the relative positions of the frame and the thrust chamber, so that the position of the thrust line is unchanged when the engine is repeatedly installed; and the 2 reference positioning holes of the upper flange plate 1 are used for positioning the relative positions of the engine hot-standard test run rack and the engine and are used as the data reference of the thrust line.
And a precise measurement mirror mounting platform is arranged on the lower flange plate 2, and a 15mm multiplied by 15mm precise measurement mirror 6 is adhered to the platform and is used for calibrating and measuring the thrust vector of the engine. The upper surface of the upper flange plate 1 is provided with correction allowance, the allowance of the upper flange plate 1 is corrected and processed (only the upper flange plate 1 is reserved, and the correction comprises thickness and aperture) according to the thrust line measuring result of the engine hot marker, the deflection amount and the translation amount of the thrust line can be accurately adjusted, and the precision target of the thrust line can be accurately controlled.
The frame of the embodiment adopts titanium alloy integrated processing, has no welding structure on the whole, has good integrated processing structural strength, and lightens the structural quality to the greatest extent on the basis of ensuring the structural strength. And the structural design of the supporting beam reduces the heat conduction channel and can reduce the heat conductivity. When the engine works, the temperature of the lower flange plate 2 can reach 200-300 ℃, so that the lower surface of the lower flange plate 2 is provided with the oxidation heat insulation layer by selecting a low-heat-conductivity material, the temperature of the upper flange can be reduced to be not more than 50 ℃ through the material heat insulation layer, the heat conduction channel is reduced through the middle structure of the frame on the basis of ensuring the structural strength, and the heat influence of the high temperature of the thrust chamber of the rocket engine on other structural components is effectively isolated.
The frame of the embodiment is used as a thrust transfer structure and a thrust vector adjusting part, the upper flange plate 1 and the lower flange plate 2 are both provided with a positioning structure for fixing the position of a thrust chamber and positioning the direction of a hot-mark thrust frame, the thrust vector of an engine is measured by hot-mark test vehicle, the reserved thickness and butt-joint aperture of the upper flange plate 1 can be processed and corrected after hot marking, the translation amount and deflection amount of a thrust line are adjusted, and the thrust line is marked by a fine measuring mirror 6 arranged on the frame; the frame of the embodiment has the functions of thrust vector adjustment and heat insulation.
The above description is only for the preferred embodiment of the present invention and does not limit the technical solution of the present invention, and any modifications made by those skilled in the art based on the main technical idea of the present invention belong to the technical scope of the present invention.
Claims (8)
1. The integral frame of the liquid rocket engine is characterized in that: the device comprises a precision measurement mirror (6), an integrally processed upper flange plate (1), a lower flange plate (2), 4 main beams, 2V-shaped side beams and 2 mounting planes;
a plurality of first butt joint holes (11) are formed in the upper flange plate (1) along the circumferential direction, wherein 2 first butt joint holes (11) are used as reference positioning holes;
the lower flange plate (2) is coaxially arranged below the upper flange plate (1), the inner diameter of the lower flange plate (2) is smaller than that of the upper flange plate (1), the outer diameter of the lower flange plate (2) is smaller than that of the upper flange plate (1), a plurality of second butt joint holes (21) are formed in the lower flange plate (2) in the circumferential direction, and a heat insulation layer and two symmetrically arranged positioning grooves are formed in the lower surface of the lower flange plate (2);
two ends of the 4 main beams are respectively connected with the upper flange plate (1) and the lower flange plate (2), the 4 main beams are uniformly distributed along the circumferential direction, and the 4 main beams are respectively a first main beam (31), a second main beam (32), a third main beam and a fourth main beam (34) which are sequentially arranged along the circumferential direction;
the 2 installation planes are respectively a first installation plane (41) and a second installation plane (42), the first installation plane (41) is arranged between the first main beam (31) and the second main beam (32), and the second installation plane (42) is arranged between the third main beam and the fourth main beam (34);
the 2V-shaped side beams are respectively a first V-shaped side beam (51) and a second V-shaped side beam (52), the first V-shaped side beam (51) is arranged between the first main beam (31) and the fourth main beam (34), and the second V-shaped side beam (52) is arranged between the second main beam (32) and the third main beam;
and the precision measurement mirror (6) is arranged on the outer side of the lower flange plate (2) and is used as a reference for thrust vector expression.
2. The liquid rocket engine monoblock frame of claim 1 wherein: the plurality of first butt joint holes (11) are 2N first butt joint holes (11) which are uniformly distributed on the circumference, N is an integer larger than or equal to 2, and the 2 reference positioning holes are symmetrically arranged.
3. A liquid rocket engine monoblock frame as defined in claim 2 wherein: the first V-shaped side beam (51) comprises a first supporting beam (511) and a second supporting beam (512), one end of the first supporting beam (511) is intersected with one end of the second supporting beam (512) and is connected to the upper flange (1), the other end of the first supporting beam (511) is arranged at the joint of the fourth main beam (34) and the lower flange (2), and the other end of the second supporting beam (512) is arranged at the joint of the first main beam (31) and the lower flange (2);
the second V-shaped side beam (52) has the same structure as the first V-shaped side beam (51), and the opening directions of the V shapes are opposite.
4. A liquid rocket engine monoblock frame as defined in any one of claims 1 to 3 wherein: the heat insulation layer is made of a low-thermal-conductivity material.
5. The liquid rocket engine monoblock frame of claim 4 wherein: each main beam is provided with a reinforcing rib (7);
the locating slot is a U-shaped key slot.
6. The liquid rocket engine monoblock frame of claim 5 wherein: the upper flange plate (1), the lower flange plate (2), 4 main beams, 2V-shaped side beams and 2 mounting planes are made of titanium alloy materials.
7. The liquid rocket engine monoblock frame of claim 6 wherein: grooves (8) are formed between two adjacent first butt joint holes (11) in the upper flange plate (1) and between two adjacent second butt joint holes (21) in the lower flange plate (2).
8. The liquid rocket engine monoblock frame of claim 1 wherein: and the first mounting plane (41) and the second mounting plane (42) are both provided with mounting holes (43).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110104339.6A CN112943482B (en) | 2021-01-26 | 2021-01-26 | Integral frame of liquid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110104339.6A CN112943482B (en) | 2021-01-26 | 2021-01-26 | Integral frame of liquid rocket engine |
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| CN112943482A true CN112943482A (en) | 2021-06-11 |
| CN112943482B CN112943482B (en) | 2022-08-12 |
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| CN202110104339.6A Active CN112943482B (en) | 2021-01-26 | 2021-01-26 | Integral frame of liquid rocket engine |
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