CN116538871A - Novel gas rudder and verification method thereof - Google Patents
Novel gas rudder and verification method thereof Download PDFInfo
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- CN116538871A CN116538871A CN202310814714.5A CN202310814714A CN116538871A CN 116538871 A CN116538871 A CN 116538871A CN 202310814714 A CN202310814714 A CN 202310814714A CN 116538871 A CN116538871 A CN 116538871A
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000012795 verification Methods 0.000 title claims abstract description 32
- 238000009413 insulation Methods 0.000 claims abstract description 69
- 238000002679 ablation Methods 0.000 claims abstract description 10
- 230000009471 action Effects 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims description 26
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 26
- 230000008569 process Effects 0.000 description 11
- 238000004088 simulation Methods 0.000 description 10
- 230000000875 corresponding effect Effects 0.000 description 8
- 238000000465 moulding Methods 0.000 description 8
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 239000002184 metal Substances 0.000 description 5
- 229910052751 metal Inorganic materials 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000001788 irregular Effects 0.000 description 3
- 239000000377 silicon dioxide Substances 0.000 description 3
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- 229910000831 Steel Inorganic materials 0.000 description 2
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- 238000001514 detection method Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000002076 thermal analysis method Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
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- 239000007787 solid Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 230000004580 weight loss Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
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- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a novel gas rudder and a verification method thereof, and belongs to the technical field of aerospace. Wherein, novel gas rudder includes: the gas rudder body is arranged at the nozzle of the engine through a steering engine box; the gas rudder body includes: the first connecting plate and the second connecting plate are vertically arranged on the first connecting plate; the first connecting plate is used for being connected with the steering engine box, and the second connecting plate is positioned at one side of the first connecting plate far away from the steering engine box; and a heat insulation structure is arranged on the second connecting plate. According to the invention, the heat insulation structure is arranged on the second connecting plate, so that the purpose of delaying the ablation time of the second connecting plate is achieved, and the gas rudder body can provide moment within a preset range for the rocket under the action of heat flow ejected by the engine, and normal flight of the rocket is ensured.
Description
Technical Field
The present disclosure relates generally to the field of aerospace technology, and in particular, to a novel gas rudder and a verification method thereof.
Background
The gas rudder is an executive component of a rocket attitude control system, when the rocket is disturbed and deviates from a preset orbit in the flight process, the control system finds out a signal to be input into the steering engine, the steering engine operates the gas rudder to change the rudder deflection angle, and the control force generated on the control surface changes the rocket attitude, so that the rocket is ensured to fly according to the preset orbit.
In the prior art, the gas rudder is generally made of tungsten-impregnated copper, has large weight and is very high in price. After transonic speed of the rocket, the control force provided by the gas rudder is smaller than the control force provided by the air rudder, the control force can be completely omitted, unnecessary weight is carried if the control force is not omitted, and resistance is increased, for example, chinese literature library discloses a gas rudder assembly (CN 210942312U), and the gas rudder assembly is characterized in that gas can be prevented from directly entering a rudder shaft by optimizing and improving the structures of a rudder body and a heat-proof body in the gas rudder assembly, the thermal environment at the rudder shaft is optimized, the normal flight of the rocket is prevented from being influenced by failure of the gas rudder, but the gas rudder assembly only considers improving the heated environment of the rudder shaft, and a connecting plate of the gas rudder is also influenced by heat flow if the heated environment of the rudder is omitted. For this purpose, we propose a new gas rudder to solve the above problems.
Disclosure of Invention
In view of the above-described drawbacks or shortcomings of the prior art, it is desirable to provide a novel gas rudder excellent in heat insulating effect and capable of providing a control torque satisfying the attitude demand, and a verification method thereof.
In a first aspect, the present invention provides a novel gas rudder for use at an engine nozzle of a rocket, the novel gas rudder comprising:
the gas rudder body is arranged at the nozzle of the engine through a steering engine box; the gas rudder body includes: the device comprises a first connecting plate and a second connecting plate vertically arranged on the first connecting plate;
the first connecting plate is used for being connected with the steering engine box;
the second connecting plate is positioned at one side of the first connecting plate far away from the steering engine box; and the second connecting plate is provided with a heat insulation structure.
The heat insulation structure is used for delaying the ablation time of the second connecting plate when the second connecting plate receives heat flow ejected from the engine nozzle, so that the gas rudder body can provide moment within a preset range for a rocket under the action of the heat flow.
According to the technical scheme provided by the invention, the method further comprises the following steps: a heat shield body coupled to the first and second connection plates;
the heat-proof body covers the outer surfaces of the first connecting plate and the second connecting plate; the heat-proof body is made of heat-proof materials.
According to the technical scheme provided by the invention, the heat insulation structure comprises: a first heat insulating unit and a second heat insulating unit;
the first heat insulating unit includes: the second connecting plate is arranged close to an opening on the edge of the engine nozzle and is provided with a bulge part formed by separating the opening;
the second heat insulating unit includes: at least one heat insulation opening arranged on the second connecting plate; a thermal resistance structure is formed between the edge of the heat insulation opening and the edge of the second connecting plate; the heat insulation port is used for isolating heat sprayed to the second connecting plate from the engine nozzle;
the heat insulation opening is inclined, and an included angle is formed between the extending direction and the first direction; the included angle opening faces the first connecting plate and is an acute angle; the first direction is a vertical direction.
According to the technical scheme provided by the invention, the second connecting plate can be divided into the heat insulation plate and the mounting plate from top to bottom along the first direction;
the heat insulation plate is provided with the heat insulation structure;
at least one first mounting hole and a first positioning hole are formed in the mounting plate; the first mounting hole is used for being connected with a rudder shaft of the steering engine box; the first positioning hole is used for positioning the relative position of the second connecting plate and the first connecting plate.
According to the technical scheme provided by the invention, the first connecting plate is provided with the second mounting hole and the second positioning hole which correspond to the first mounting hole and the first positioning hole.
In a second aspect, the present invention provides a verification method of a novel gas rudder, which is applied to the novel gas rudder, and the verification method includes the following steps:
constructing a first model and a second model; the first model is constructed according to original gas rudder parameters, and the second model is constructed according to novel gas rudder parameters; wherein the novel gas rudder parameters at least comprise the material and specification of the first connecting plate and the second connecting plate;
placing the first model in a first operating condition, the first operating condition comprising: the method comprises the steps that an engine state, a flight environment parameter, a gas rudder wall temperature and a plurality of groups of rudder deflection angles of the first model are in the engine state, the flight environment parameter and the gas rudder wall temperature;
acquiring a set of aerodynamic force values born by the first model under the first working condition; the aerodynamic force value set comprises a plurality of aerodynamic force values corresponding to each group of rudder deflection angles;
and taking the aerodynamic force value as a performance verification value of the second model, and judging whether the strength and the heat insulation degree of the second model are in a qualified range or not.
According to the technical scheme provided by the invention, before the step of placing the first model in the first working condition, the method further comprises the following steps:
disposing the first model at a spout of an engine model;
and establishing a rudder deflection reference coordinate system by taking the intersection point of the rudder shaft of the first model and the central axis of the engine model as an origin, wherein the rudder deflection reference coordinate system is used for calibrating the aerodynamic direction of the aerodynamic value.
According to the technical scheme provided by the invention, the step of judging the strength of the second model by taking the aerodynamic force value as the performance verification value of the second model comprises the following steps:
selecting the maximum aerodynamic force value in the same aerodynamic force direction in the aerodynamic force value set;
applying aerodynamic force corresponding to the maximum aerodynamic force value to the second model, and collecting stress values of the first connecting plate and the second connecting plate of the second model;
and judging that the stress value is smaller than a preset stress value, and confirming that the material strength of the second model is qualified.
According to the technical scheme provided by the invention, the step of judging the heat insulation degree of the second model by taking the aerodynamic force value as the performance verification value of the second model further comprises the following steps:
selecting the maximum aerodynamic force value in the same aerodynamic force direction in the aerodynamic force value set;
applying a pneumatic heat flow to the second model with the maximum aerodynamic force value as a pneumatic heat flow value;
and judging that the temperature value of the first connecting plate and the second connecting plate of the second model under the action of the pneumatic heat flow is smaller than a preset temperature value, and confirming that the material heat insulation degree of the second model is qualified.
According to the technical scheme provided by the invention, the stress value and the temperature value are used for guiding parameter adjustment of the second model, and the parameter adjustment comprises the following steps: and replacing materials with different strength or heat conductivity, and increasing the size of the first connecting plate and the second connecting plate of the second model.
In summary, the technical scheme specifically discloses a novel gas rudder and a verification method thereof. Wherein, novel gas rudder includes: the gas rudder body is arranged at the nozzle of the engine through a steering engine box; specifically, the gas rudder body comprises a first connecting plate and a second connecting plate vertically arranged on the first connecting plate; the first connecting plate is used for being connected with the steering engine box, and the second connecting plate is located one side, away from the steering engine box, of the first connecting plate.
The invention mainly controls the posture of the rocket through the gas rudder during the present solid rocket take-off, so the rocket needs to provide enough control moment through the gas rudder in subsonic and transonic speed intervals after taking-off, therefore, the invention is used for delaying the ablation time of the second connecting plate when the second connecting plate receives the heat flow ejected from the engine nozzle by arranging the heat insulation structure on the second connecting plate, so that the gas rudder body can provide the moment meeting the posture control requirement for the rocket under the action of the heat flow, and the normal take-off of the rocket is ensured.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, made with reference to the accompanying drawings in which:
fig. 1 is a schematic view of a first structure of a novel gas rudder.
Fig. 2 is a schematic structural view of a second connecting plate in the novel gas rudder.
Fig. 3 is a schematic structural view of a first connection plate in a novel gas rudder.
Fig. 4 is a schematic view of a second structure of a novel gas rudder.
Fig. 5 is a schematic diagram of a novel gas rudder connected to a steering engine box.
Fig. 6 is a schematic flow chart of a verification method of a novel gas rudder.
FIG. 7 is a schematic illustration of aerodynamic force direction calibration of a novel gas rudder aerodynamic force value.
FIG. 8 is a graphical representation of the results of a material property test of a second model constructed from novel gas rudder parameters.
FIG. 9 is a graphical illustration of the results of a constant temperature test of a first model constructed from raw rudder parameters.
Fig. 10 is a graphical illustration of the results of a constant temperature test of a second model constructed from the novel rudder parameters.
Fig. 11 is a schematic diagram of the results of a aerodynamic heat flow test of a second model constructed from the novel rudder parameters.
Reference numerals in the drawings: 100. a gas rudder body; 101. a first connection plate; 102. a second connecting plate; 102-1, a heat insulation board; 102-2, mounting plate; 103. a thermal resistance structure; 104. a heat insulation port; 105. a first mounting hole; 106. a first positioning hole; 107. a second mounting hole; 108. a second positioning hole; 109. molding the fixing hole; 200. steering engine box; 300. a heat-resistant body; 400. an engine.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the invention are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Example 1
Please refer to fig. 1 and fig. 5, which illustrate a first structural schematic diagram of a novel gas rudder and a connection schematic diagram of the novel gas rudder and a steering engine box according to the present embodiment, wherein the novel gas rudder includes:
the gas rudder body 100, the gas rudder body 100 is set up in the engine nozzle through the steering engine box 200; the gas rudder body 100 includes: a first connection plate 101 and a second connection plate 102 vertically provided on the first connection plate 101;
the first connecting plate 101 is used for being connected with the steering engine box 200;
the second connecting plate 102 is positioned on one side of the first connecting plate 101 away from the steering engine box 200; the second connecting plate 102 is provided with a heat insulation structure;
the heat insulation structure is used for delaying the ablation time of the second connection plate 102 when the second connection plate 102 is subjected to the heat flow ejected from the engine nozzle, so that the gas rudder body 100 can provide moment within a preset range for the rocket under the action of the heat flow.
The gas rudder is an executive component of a rocket attitude control system, when the rocket is disturbed and deviates from a preset orbit in the flight process, the rocket control system can send a signal to be input into the steering engine, the steering engine operates the gas rudder to change the rudder deflection angle, and the control force generated on the control surface changes the rocket attitude, so that the rocket is ensured to fly according to the preset orbit. However, since the gas rudder is disposed at the nozzle of the rocket engine, it is necessary to ensure that the gas rudder has good heat insulation (temperature resistance), and ensure that the gas rudder body 100 is not ablated when the rocket is subjected to the heat flow ejected from the nozzle of the engine, when the rocket uses the gas rudder as the main actuator for controlling the attitude of the rocket (before transonic speed of the rocket), so as to provide sufficient control torque for the rocket, the gas rudder control torque is mainly positively correlated with the area of the vertical plate (corresponding to the second connecting plate 102) of the gas rudder, and generally, the second connecting plate 102 has an area not less than 50% of the initial area before transonic speed of the rocket, so that the control torque can be provided for the rocket, and the attitude of the rocket before transonic speed of the rocket is ensured to be stable.
As shown in fig. 1, in this embodiment, a novel gas rudder is specifically provided, and a gas rudder body 100 includes: a first connection plate 101 and a second connection plate 102 vertically provided on the first connection plate 101; the first connecting plate 101 provides support for the second connecting plate 102, and the first connecting plate 101 is connected with the steering engine box 200, so that the first connecting plate 101 also plays a role of flame shielding for the steering engine shaft.
The second connecting plate 102 is a main plate for guaranteeing ruddiness, provides moment meeting gesture requirements for the rocket through different deflections, is provided with a heat insulation structure capable of delaying ablation time of the second connecting plate 102 in order to guarantee that the second connecting plate 102 cannot be thermally disabled before transonic speed, and when the rocket transonic speed is achieved, control force provided by a gas rudder is smaller than control force provided by an air rudder, at the moment, heat flow ejected by the rocket exceeds bearing capacity of the heat insulation structure, ablation of the gas rudder is achieved, but the heat flow is equivalent to unnecessary weight loss, and resistance of rocket flight is reduced.
As shown in fig. 4, further includes: a heat shield 300 coupled to the first connection plate 101 and the second connection plate 102;
the heat-proof body 300 covers the outer surfaces of the first connection plate 101 and the second connection plate 102; the heat-proof body 300 is made of a heat-proof material, and optionally, the heat-proof material is high silica, so that the heat-proof body 300 can further protect the second connecting plate 102 from being rapidly ablated.
In an actual process, the heat-proof body 300 is covered on the first connecting plate 101 and the second connecting plate 102 through a molding process, as shown in fig. 2, the second connecting plate 102 is further provided with a molding fixing hole 109, and the hole diameter of the molding fixing hole 109 is relatively large, so that when the first connecting plate 101 and the second connecting plate 102 are connected, the heat-proof body 300 is wrapped outside the first connecting plate through the molding process, and the heat-proof body 300 also penetrates through the molding fixing hole 109, so that the heat-proof body 300 is prevented from being combined with the second connecting plate 102 in an insufficiently tight manner after being molded.
As shown in fig. 1 and 2, the heat insulation structure includes: a first heat insulating unit and a second heat insulating unit; when the heat-proof layer 300 is ablated by the heat flow, the second connection plate 102 and the first connection plate 101 are exposed, and the heat-proof structure needs to be arranged on the second connection plate 102 because the second connection plate 102 is in maximum contact with the heat flow, so that the second connection plate 102 cannot completely fail thermally before transonic speed.
The first heat insulating unit includes: a protruding part which is arranged on the edge of the second connecting plate 102, close to the nozzle edge of the engine and is formed by separating the openings;
the second heat insulating unit includes: at least one heat insulation opening 104 arranged on the second connecting plate 102, and a heat resistance structure 103 is formed between the heat insulation opening 104 and the edge of the second connecting plate 102; the heat insulation port 104 is used for insulating heat sprayed from the engine nozzle to the second connecting plate 102; specifically, the formation position of the thermal resistance structure 103 can be seen at the circle mark of fig. 1;
the heat insulation opening 104 is inclined, and an included angle is formed between the extending direction and the first direction; the angle opening is oriented towards the first connecting plate 101 and is acute, where the first direction is vertical, see in particular the direction of arrow B in fig. 1.
In particular, the first insulating unit is understood to be a first insulating unit designed with an irregularly running edge on the edge of the second connecting plate 102 close to the engine nozzle, see in particular fig. 2, a curved edge on the left side of the second connecting plate 102, which is formed by an opening and a bulge formed by the separation of the openings.
In addition, since the irregular edge of the second connecting plate 102 is closest to the engine nozzle, in order to improve the heat insulation effect of the second connecting plate 102, a second heat insulation unit is further arranged on the plate surface of the second connecting plate 102, and the second heat insulation unit can ensure that the rear half metal part (the metal part on the right side of the heat insulation opening 104) of the second connecting plate 102 cannot be thermally failed before transonic speed, so that enough control moment is provided for the rocket.
Specifically, the second heat insulating unit includes: at least one heat insulation opening 104 arranged on the second connecting plate 102, as can be seen from fig. 1, two heat insulation openings 104 of the novel gas rudder are arranged; the heat insulation port 104 can isolate heat sprayed to the second connecting plate 102 from the engine nozzle, and can assist the heat-proof body 300 to be better combined with the second connecting plate 102 after being molded, because the heat-proof body 300 penetrates through the heat insulation port 104 after being molded.
The explanation about the heat resistance structure 103 is as follows: the heat resistance structure 103 is arranged in the second connecting plate 102, so that the heat transfer of the engine nozzle between the front part and the rear part of the second connecting plate 102 is greatly reduced; specifically, the cross-sectional area of the metal at the joint of the front and rear parts of the second connecting plate 102 is reduced to the greatest extent under the condition of allowable strength, and the thermal resistance structure 103 is formed, so that the heat transfer speed of heat is reduced when the heat passes through the thermal resistance structure 103, and the failure of overheat strength caused by heat transfer of the rear half part of the second connecting plate 102 is avoided.
As shown in fig. 2, the inclined design of the heat insulation opening 104 can not only increase the length of the heat insulation opening 104, but also lay a foundation for forming the heat resistance structure 103; specifically, the inclined heat insulation opening 104 and the irregular edge can make the heat insulation opening 104 and the edge of the second connecting plate 102 have different distances, and in the actual design process, the metal cross-sectional area between the heat insulation opening 104 and the edge of the second connecting plate 102 is narrowed to form a heat resistance structure, so as to further improve the heat insulation effect of the second connecting plate 102.
As shown in fig. 2, the second connecting plate 102 may be divided into a heat insulation plate 102-1 and a mounting plate 102-2 from top to bottom along the first direction, where the heat insulation plate 102-1 and the mounting plate 102-2 respectively correspond to two dashed areas; wherein the heat insulation plate 102-1 is a main area for guaranteeing rudder efficiency of the gas rudder, and the mounting plate 102-2 is an area connected with the first connecting plate 101; here, the first direction is a vertical direction, and can be specifically referred to as arrow pointing at B in fig. 1.
Specifically, the heat insulation plate 102-1 is provided with the heat insulation structure;
the mounting plate 102-2 is provided with at least one first mounting hole 105 and a first positioning hole 106; the first mounting hole 105 is used for being connected with a rudder shaft of the steering engine box 200; the first positioning hole 106 is used for positioning the relative position of the second connecting plate 102 and the first connecting plate 101.
In practical application, the first mounting hole 105 is used for assisting the linking and fixing of the second connecting plate 102, the first connecting plate 101 and the rudder shaft of the steering engine box; the first positioning hole 106 is a positioning pin hole and is used for positioning the first connecting plate 101 and the second connecting plate 102, so that the first connecting plate 101 and the second connecting plate 102 are ensured to be accurately fixed during high silica molding, and molding efficiency is improved.
As shown in fig. 3, the first connecting plate 101 is provided with a second mounting hole 107 and a second positioning hole 108 corresponding to the first mounting hole 105 and the first positioning hole 106, and the second mounting hole 107 and the second positioning hole 108 are respectively used for being matched with the first mounting hole 105 and the second positioning hole 106 to complete positioning and mounting of the first connecting plate 101 and the second connecting plate 102.
Example 2
As shown in fig. 6, a verification method of a novel gas rudder based on the novel gas rudder of embodiment 1, the verification method comprising the steps of:
s1, constructing a first model and a second model; the first model is built according to original gas rudder parameters, and the second model is built according to novel gas rudder parameters; wherein, the novel gas rudder parameters at least comprise the materials and specifications of the first connecting plate 101 and the second connecting plate 102;
s2, placing the first model in a first working condition, wherein the first working condition comprises: the engine state, the flight environment parameters, the gas rudder wall temperature and the first model are in the engine state, the flight environment parameters and the multiple groups of rudder deflection angles of the gas rudder wall temperature;
s3, acquiring a set of aerodynamic force values of the first model under a first working condition; the aerodynamic force value set comprises a plurality of aerodynamic force values corresponding to each group of rudder deflection angles;
s4, taking the aerodynamic force value as a performance verification value of the second model, and judging whether the strength and the heat insulation degree of the second model are in a qualified range.
The embodiment specifically provides an implementation mode of a verification method of a novel gas rudder, mainly comprising the steps that a first connecting plate 101 and a second connecting plate 102 of the gas rudder are required to be free from structural failure within a preset duration in rocket flight, and control moment is provided; after the preset time, the control force of the rocket is switched to be dominated by the air rudder, so that the whole second connecting plate 102 is partially ablated and depleted after the preset time, and the load of the rocket is reduced; here, the preset time period is 10s.
It should be noted that, in the present invention, verification is performed mainly that the second connection board 102 is capable of not generating structural failure within a preset period of time, and specifically, it is verified whether the strength and the heat insulation degree of the gas rudder body 100 meet the requirements; because whether the second web 102 is ablated immediately after a predetermined period of time or to slow down a little of time is merely to lighten the load of the rocket, it is an insignificant factor compared to providing the rocket with a moment satisfying the attitude.
Specifically, combining the step S2 and the step S3, placing a first model constructed by original gas rudder parameters under a first working condition, and obtaining a set of aerodynamic force values of the first model under the first working condition;
the first working condition is, for example, the following condition:
engine state: average expansion ratio of engine: (10.64); flight environment parameters: h=1km ma0.3; gas rudder wall temperature: 300K; the environment is a main working condition environment of the gas rudder, and aiming at the subsonic flight stage of the rocket just taking off, the air rudder can not provide control rudder efficiency in the subsonic environment, and the rocket is controlled by the gas rudder completely; the plurality of groups of rudder deflection angles are optionally: 0 °, 10 ° and 20 °;
in the actual verification process, aerodynamic force value sets of the first model under the first working condition can be obtained by using simulation software (such as NSAAS and the like), and the aerodynamic force value sets are shown in the following table after splitting:
TABLE 1 aerodynamic forces experienced by the first model along the X-direction
TABLE 2 aerodynamic forces experienced by the first model in the Y-direction
TABLE 3 aerodynamic forces experienced by the first model along the Z-direction
As can be seen from the combination of table 1, table 2 and table 3, each set of rudder deflection angles comprises a plurality of aerodynamic force values; each aerodynamic force value corresponds to three channel types of dP, dY and dR respectively; specifically, dP represents the pitch channel; dY represents a yaw path; dR represents a roll channel; accordingly, rudder deflection angles actually cover pitch, yaw and roll channels that are offset by 0 °, 10 ° and 20 ° in the respective offset directions, respectively, wherein the pitch channel is used to control the rocket to move up and down, the yaw channel is used to control the rocket to move left and right, and the roll channel is used to control the rocket to rotate about its axis.
Specifically, in step S4, the strength and the heat insulation degree of the second model are applied to the second model according to the aerodynamic force value obtained by the first model under the first working condition, and it is further verified whether the materials, specifications, etc. of the first connecting plate 101 and the second connecting plate 102 of the second model meet the test requirements. According to the method, the first model is collected in advance, collected data is used as verification values to be applied to the second model, objectivity of test data is guaranteed, and meanwhile accuracy of verifying performance of the second model is further improved.
In step S2: before the step of placing the first model in the first operating condition, further comprising:
disposing a first mold at a nozzle of an engine mold;
and establishing a rudder deflection reference coordinate system by taking the intersection point of the rudder shaft of the first model and the central axis of the engine model as an origin, wherein the rudder deflection reference coordinate system is used for calibrating the direction of aerodynamic force values.
Specifically, the above steps need to be combined with tables 1, 2 and 3, and since tables 1 to 3 represent aerodynamic forces applied to the first model in different directions, respectively, different aerodynamic force values need to be distinguished in directions according to the differences of aerodynamic force acquisition points, so the following coordinate system is established.
Further, as shown in fig. 7, the origin of the coordinate system is located at the intersection point of the rudder shaft of the gas rudder and the model axis of the engine 400, the X direction is the direction parallel to and pointing to the rocket body, the Y direction is the direction perpendicular to and pointing upward to the rocket body, and the Z direction is the arrow direction pointing to the upper right. In this coordinate system, the X direction is understood to be directed from the rear of the rocket body toward the head, so that in a conventional coordinate system, the axial force applied to the rocket should theoretically be negative, but in accordance with the conventional axial force sign, the axial force directed from the rocket head toward the rear will be defined as positive.
In step S4: a step of judging the intensity of the second model by taking the aerodynamic force value as a performance verification value of the second model, comprising:
selecting the value of the maximum aerodynamic force in the same aerodynamic force direction in the aerodynamic force value set;
applying maximum aerodynamic force to the second model, and collecting stress values of the first connecting plate 101 and the second connecting plate 102 of the second model;
and judging that the stress value is smaller than a preset stress value, and confirming that the material strength of the second model is qualified.
Specifically, in the actual test process, verifying the strength of the second model, performing strength verification on the combined metal core mold by adopting a statics method, under the corresponding working condition, taking the maximum aerodynamic force value in the same aerodynamic force direction as a verification value, inputting the verification value into a simulation system to perform strength verification on the second model, and when the first connecting plate 101 and the second connecting plate 102 of the second model can bear the input aerodynamic force, indicating that the material strength of the second model is qualified; taking tables 1, 2 and 3 as examples, aerodynamic forces of magnitude 6064.57 can be applied to the second model at rudder deflection angles of 10 °.
For example, in the actual test process, the first connecting plate 101 and the second connecting plate 102 of the second model are simulated by adopting Q345 steel, the material Q345 steel has the maximum stress 345MPa of elastic deformation, and the breaking stress is 470MPa; finally taking the simulation situation when the rudder deflection angle is 10 degrees as an example, the simulation result is: the maximum stress value to which the first connection plate 101 is subjected is 42MPa; the maximum stress value to which the second connecting plate 102 is subjected is 30MPa; wherein, during the simulation test, the stress concentration position of the second connecting plate 102 is shown in fig. 8. The above simulation results indicate that the performance of material Q345 is within the maximum allowable stress range.
Specifically, step S4: the step of taking the aerodynamic force value as the performance verification value of the second model, wherein the step of judging the heat insulation degree of the second model specifically comprises the following steps:
selecting the maximum aerodynamic force value in the same aerodynamic force direction in the aerodynamic force value set;
applying a pneumatic heat flow to the second model with the maximum aerodynamic force value as a pneumatic heat flow value;
and judging that the temperature values of the first connecting plate 101 and the second connecting plate 102 of the second model under the action of the pneumatic heat flow are smaller than the preset temperature value, and confirming that the material heat insulation degree of the second model is qualified.
In the actual test process, the corresponding heat-proof bodies 300 are already added to the first model and the second model, and the heat-proof bodies 300 are not important factors in the previous strength test because the heat-proof bodies 300 are mainly used for heat protection. Because pneumatic thermal analysis hardly simulates the scouring effect of metal particles when an engine works, the scheme is divided into two parallel reference calculations when thermal simulation analysis is carried out: (1) Comparing the heating degrees of the first model and the second model at the constant temperature; (2) And applying pneumatic heat flow to the second model by taking the maximum aerodynamic force value as a pneumatic heat flow value.
Specifically, in the constant temperature heating analysis, referring to data in a simulation report of a certain type of gas rudder, setting a constant temperature T=1925 ℃ on a windward side for simulation; the simulation time length is 20s, which covers the working time 11.2 s of a certain engine, wherein the simulation time length can be adjusted according to the working time lengths of different engines, and it is noted that the selection of the engine model can be matched with the engine state in the first working condition.
With reference to fig. 9 and 10, the test structure shows, at a constant temperature t=1925 ℃ under thermal analysis:
the first model is made of tungsten with high thermal conductivity, so that the temperature of a detection point on the back surface of the first connecting plate 101 is approximately 5 s and is close to the thermal balance, and the temperature reaches 1881.3 ℃;10 s reaches 1923.5 ℃;20 s reaches 1925 ℃.
The temperature of the detection point at the back of the bottom plate of the first connecting plate 101 of the second model is not increased when the temperature is 20s, and the temperature is still 22 ℃ at normal temperature.
Wherein, the abscissa of fig. 9 and 10 represents time in s; the ordinate is both expressed as temperature in degrees celsius.
In a test environment in which the maximum aerodynamic force value is taken as the aerodynamic heat flow value and the aerodynamic heat flow is applied to the second model, the test result is as follows, in combination with fig. 11:
the maximum temperature of the front edge of the second connecting plate 102 of the gas rudder corresponding to the second model reaches 2854 ℃, and the first connecting plate 101 forms two laser high temperature areas due to high-speed flushing. Comparing the temperature distribution at times t=1s, t=10s and t=20s under the constant temperature boundary condition, because the material of the heat shield 300 covered outside the second model is high silica, the heat shield has lower heat conductivity, the highest temperature reached by the first connecting plate 101 and the second connecting plate 102 in a short time of 20s is 31 ℃, and meanwhile, the first connecting plate 101 and the second connecting plate 102 also do not find thermal failure (after the test, the shapes of the first connecting plate 101 and the second connecting plate 102 are kept consistent with the initial state, and phenomena such as melting and the like do not occur).
As described in the experiments of strength and heat insulation, the obtained stress value and the obtained temperature value can be used to guide the parameter adjustment of the second model, for example, to replace materials with different strength or heat conductivity and to increase the sizes of the first connection board 101 and the second connection board 102 when the second model performs performance verification.
Specifically, experiments regarding changing the dimensions of the first connection plate 101 and the second connection plate 102, which in turn may change the rudder efficiency, are as follows:
two test models were also built (the most important difference between the two models is the rudder plate thickness) for comparison of rudder performance (Fx and Fy are used to refer to forces in all directions, as known from the coordinate system built above). As can be seen from the combination of Table 4, the axial force of the first test model under the rudder deflection angle of zero is 2.7 times that of the second test model, and the rudder efficiency of the pitching channel is about 82% -84% of that of the second test model. The main difference between the two is that the rudder thickness of the first test model is more than 1 time greater than that of the second test model, and in addition, the front edge of the second model is more gentle due to the increase of the rudder plate thickness, and the front edge of the first model is close to the pointed front edge.
Table 4 comparison of the test model for rudder performance in pitch passage
In summary, in the second model test process, different verification data obtained can assist the technician to make targeted adjustment on the novel gas rudder, for example, the thickness of the second connecting plate can be properly increased to improve the rudder efficiency; and materials with lower heat conductivity can be replaced by improving the heat insulation effect.
Example 3
Based on example 2, at its step S4: the step of judging the heat insulation degree of the second model by taking the aerodynamic force value as the performance verification value of the second model can also set verification of a third model, wherein the third model is an ablation model deduced to be formed based on the second model; specifically, the deduction process is to obtain a second model which is obtained by deduction and assumption according to the ablation form of the first model, and the second model is subjected to ablation at a certain moment.
In the constant temperature heating analysis, a heat flow test of applying a constant temperature of T=1925 ℃ on the windward side can be performed by using a third model instead of the second model, and the heat insulation effect of the second model after the heat shield 300 is partially ablated and continuously heated for 20 seconds is observed; since the heat insulation of the second model is already optimized to a certain extent (the design of the heat insulation structure or the material selection of the heat-proof body 300, etc.) at the beginning of the establishment of the first model and the second model, the second model and the first model are directly compared, and the final test result is necessarily that the second model is better than the first model, so that the third model can be directly established to be compared with the first model, and the heated distribution situation of the third model is observed, for example, after the test is finished, it is found that the temperature reached at the irregular edge of the second connecting plate 102 is the highest and the risk of exceeding the melting point of the material exists, and the technician can perform operations of increasing the thickness of the second connecting plate 102 or replacing the material, etc. according to the test result.
The above description is only illustrative of the preferred embodiments of the present invention and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the invention referred to in the present invention is not limited to the specific combinations of the technical features described above, but also covers other technical features formed by any combination of the technical features described above or their equivalents without departing from the inventive concept. Such as the above-mentioned features and the technical features disclosed in the present invention (but not limited to) having similar functions are replaced with each other.
Claims (10)
1. A novel gas rudder applied to an engine nozzle of a rocket, the novel gas rudder comprising:
the gas rudder body (100), the gas rudder body (100) is set up in the said engine spout through the steering wheel box (200); the gas rudder body (100) includes: a first connection plate (101) and a second connection plate (102) vertically arranged on the first connection plate (101);
the first connecting plate (101) is used for being connected with the steering engine box (200);
the second connecting plate (102) is positioned at one side of the first connecting plate (101) away from the steering engine box (200); a heat insulation structure is arranged on the second connecting plate (102);
the heat insulation structure is used for delaying the ablation time of the second connecting plate (102) when the second connecting plate (102) receives heat flow sprayed from the engine nozzle, so that the gas rudder body (100) can provide moment within a preset range for a rocket under the action of the heat flow.
2. A novel gas rudder according to claim 1, further comprising: a heat shield (300) that is connected to the first connection plate (101) and the second connection plate (102);
the heat-proof body (300) covers the outer surfaces of the first connecting plate (101) and the second connecting plate (102); the heat shield (300) is a heat shield material.
3. A new gas rudder according to claim 2 wherein said insulating structure comprises: a first heat insulating unit and a second heat insulating unit;
the first heat insulating unit includes: the second connecting plate (102) is close to an opening on the edge of the engine nozzle and is provided with a bulge part formed by separating the opening;
the second heat insulating unit includes: at least one heat insulation opening (104) arranged on the second connecting plate (102); a thermal resistance structure (103) is formed between the edge of the heat insulation opening (104) and the edge of the second connecting plate (102); the heat insulation port (104) is used for insulating heat sprayed from the engine nozzle to the second connecting plate (102);
the heat insulation opening (104) is inclined, and an included angle is formed between the extending direction and the first direction; the included angle opening is towards the first connecting plate (101) and is an acute angle; the first direction is a vertical direction.
4. A new gas rudder according to claim 3, characterized in that said second connecting plate (102) is divided in said first direction from top to bottom into a heat insulating plate (102-1) and a mounting plate (102-2);
the heat insulation plate (102-1) is provided with the heat insulation structure;
at least one first mounting hole (105) and a first positioning hole (106) are formed in the mounting plate (102-2); the first mounting hole (105) is used for being connected with a rudder shaft of the steering engine box (200); the first positioning hole (106) is used for positioning the relative position of the second connecting plate (102) and the first connecting plate (101).
5. The novel gas rudder according to claim 4, wherein the first connecting plate (101) is provided with a second mounting hole (107) and a second positioning hole (108) corresponding to the first mounting hole (105) and the first positioning hole (106).
6. A method of validating a new gas rudder, applied to a new gas rudder according to any one of claims 1-5, comprising the steps of:
constructing a first model and a second model; the first model is constructed according to original gas rudder parameters, and the second model is constructed according to novel gas rudder parameters; wherein the novel gas rudder parameters at least comprise the material and specification of the first connecting plate (101) and the second connecting plate (102);
placing the first model in a first operating condition, the first operating condition comprising: the method comprises the steps that an engine state, a flight environment parameter, a gas rudder wall temperature and a plurality of groups of rudder deflection angles of the first model are in the engine state, the flight environment parameter and the gas rudder wall temperature;
acquiring a set of aerodynamic force values born by the first model under the first working condition; the aerodynamic force value set comprises a plurality of aerodynamic force values corresponding to each group of rudder deflection angles;
and taking the aerodynamic force value as a performance verification value of the second model, and judging whether the strength and the heat insulation degree of the second model are in a qualified range or not.
7. The method of claim 6, wherein prior to the step of placing the first model in the first operating mode, further comprising:
disposing the first model at a spout of an engine model;
and establishing a rudder deflection reference coordinate system by taking the intersection point of the rudder shaft of the first model and the central axis of the engine model as an origin, wherein the rudder deflection reference coordinate system is used for calibrating the aerodynamic direction of the aerodynamic value.
8. The method according to claim 7, wherein the step of determining the strength of the second model using the aerodynamic force value as the performance verification value of the second model comprises:
selecting the maximum aerodynamic force value in the same aerodynamic force direction in the aerodynamic force value set;
applying aerodynamic force corresponding to the maximum aerodynamic force value to the second model, and collecting stress values of the first connecting plate (101) and the second connecting plate (102) of the second model;
and judging that the stress value is smaller than a preset stress value, and confirming that the material strength of the second model is qualified.
9. The method according to claim 8, wherein the step of determining the heat insulation degree of the second model by using the aerodynamic force value as the performance verification value of the second model further comprises:
selecting the maximum aerodynamic force value in the same aerodynamic force direction in the aerodynamic force value set;
applying a pneumatic heat flow to the second model with the maximum aerodynamic force value as a pneumatic heat flow value;
and judging that the temperature value of the first connecting plate (101) and the second connecting plate (102) of the second model under the action of the pneumatic heat flow is smaller than a preset temperature value, and confirming that the material heat insulation degree of the second model is qualified.
10. A method of validating a new gas rudder according to claim 9 wherein said stress value and said temperature value are used to guide the adjustment of parameters of said second model, said parameter adjustment comprising: -exchanging materials of different strength or thermal conductivity and-increasing the dimensions of the first (101) and second (102) connection plates of the second model.
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