CN104598696A - High-speed missile shape design method for pressure center adjustment - Google Patents
High-speed missile shape design method for pressure center adjustment Download PDFInfo
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- CN104598696A CN104598696A CN201510065577.5A CN201510065577A CN104598696A CN 104598696 A CN104598696 A CN 104598696A CN 201510065577 A CN201510065577 A CN 201510065577A CN 104598696 A CN104598696 A CN 104598696A
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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
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a high-speed missile shape design method for pressure center adjustment. The method comprises the following steps: 1, determining global parameters of a missile and a pressure center design criteria of the missile; 2, determining a shape structure without a tail section missile; 3, additionally arranging a tail section at the tail part of a missile body and determining the shape structure with the tail section missile. According to the method, the design problem that the pressure center cannot be matched with mass center caused by the fixed shape design of the high-speed missile is solved, and particularly the missile design problems of simultaneous high requirements on stability of the missile at a separation initial flight stage and maneuverability of a maneuvering process are solved.
Description
Technical field
The present invention relates to a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate.
Background technology
The pressure heart and barycenter matched design are the important contents of high-speed missile (main flight Mach number is more than 1.0) collectivity Scheme Design, and the good pressure heart and barycenter matching performance are to guaranteeing that guided missile has good maneuverability and stability has great role simultaneously.But large and barycenter changes high-speed missile greatly for flight Mach number span, obtain the good pressure heart and barycenter matching performance more difficult often.
Current high-speed missile generally adopts fixed profile to design, like this under identical Mach number and attitude angle, the guided missile pressure heart is constant, and barycenter is along with fuel consumption is in continuous change, the nonadjustable configuration design of this pressure heart often limits the pressure heart and barycenter matching performance, and then affects the ballistic flight performance of guided missile and overall operational performance.
For the guided missile be separated from female bullet, or the guided missile of launched by airplane, be separated initial flight stage relatively fully loaded barycenter at guided missile to need to ensure certain steady state stability, and guided missile relatively unloaded barycenter when the end game needs to ensure certain maneuverability, because the relatively fully loaded barycenter of the unloaded barycenter of guided missile generally has certain reach change, employing fixed profile designs, and satisfied separation initial flight stage stability and mobile process maneuverability will become difficulty simultaneously.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate; This method solve the pressure heart design challenges of mating bad with barycenter that the design of high-speed missile fixed profile is brought, especially solve guided missile and require a high Missile Design difficult problem in separation initial flight stage stability and mobile process maneuverability simultaneously.
For solving the problems of the technologies described above, the present invention adopts following technical proposals:
The high-speed missile Exterior Surface Design regulated for pressing the heart, it comprises the steps:
Step 1, determines the population parameter of guided missile and the pressure heart design objective of guided missile;
Step 2, determines the contour structures not with rear guided missile;
Step 3, increases by a rear at the afterbody of missile airframe, and determines the contour structures being with rear guided missile.
Further, described method also comprises:
Step 4, determines the practical flight scheme of guided missile, is specially, and in the initial flight stage after guided missile is separated, now guided missile flies, for increasing the stability in guided missile initial flight stage with the configuration state of band rear guided missile determined in step 3;
When the guided missile initial flight stage terminates or end mobile needs to obtain high maneuver, under the effect of shedding separating mechanism, rear from the portion of guided missile from, after this in maneuvering flight process, guided missile flies with the configuration state not with rear guided missile determined in step 2, make like this in maneuvering flight process, entirely to suppress heart reach, and ensure good maneuverability.
Further, the population parameter of described guided missile comprises flight Mach number, height and the angle of attack of guided missile after isolation in initial flight stage and maneuvering flight process two kinds of situations;
The pressure heart design objective of described guided missile comprises the guided missile pressure heart designing requirement of guided missile in initial flight stage and maneuvering flight process two kinds of situations after isolation.
Further, the contour structures not with rear guided missile is determined in described step 2, be specially: according to the population parameter of the determined guided missile of step 1 and the pressure heart design objective of guided missile, design meets the contour structures not with rear guided missile that heart designing requirement pressed by guided missile in maneuvering flight process, and it comprises by determining that body bus geometric parameter and rudder face geometric parameter determine guided missile profile; Wherein body bus geometric parameter comprises body maximum gauge, body length and body bus curvilinear equation; Described rudder face geometric parameter comprises the section shape of the chord length of rudder face, the length of rudder face and rudder face.
Further, described step 3 is specially, and increases by a rear at the afterbody of missile airframe, and determines the contour structures being with rear guided missile, the contour structures of this band rear guided missile to meet in step 1 determine the population parameter of guided missile and the pressure heart design objective of guided missile.
Further, the contour structures of described rear is the tail skirt structure with angle of flare θ, and the diameter of ending place of this tail skirt structure is D2, the diameter of the section start of tail skirt structure is D1; The described angle of flare is θ, and θ >0 °; The diameter D2 of ending place of tail skirt structure is D2/D1 with the ratio of the diameter D1 of the section start of tail skirt structure, and D2/D1>1.0.
Further, the diameter D1 of the section start of tail skirt structure is equal with the body base diameter D not with rear guided missile determined in described step 2.
The present invention compared with prior art, has following actively useful effect:
1, the present invention adopts separable rear to design, and is designed thus reach the object of pressing the heart to regulate by guided missile shape variable.
2, the inventive method is simple, sheds separation and is easy to realize; Rear design, at the most afterbody of body, is shed to be separated and is easily realized, and can not produce obviously interference to front bomb body.
3, the pressure heart regulating effect of guided missile is obvious, and regulated quantity is easy to adjustment as required, is specially: by increasing rear at missile tail, rear is away from the centroid distance of guided missile, and the pressure heart regulating effect of guided missile can be more obvious; By adjusting tail skirt diameter and expansion angle, the pressure heart regulated quantity meeting actual needs easily can be obtained.
Accompanying drawing explanation
Fig. 1 is the contour structures schematic diagram of band rear guided missile of the present invention.
Fig. 2 be with in the present invention rear guided missile and existing be not with rear guided missile after isolation in initial flight stage and maneuvering flight process two kinds of situations guided missile press heart property calculation Comparative result figure.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described.
As shown in Figure 1, 2, a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate, it comprises the steps:
Step 1, determines the population parameter of guided missile and the pressure heart design objective of guided missile;
The population parameter of described guided missile comprises flight Mach number, height and the angle of attack of guided missile after isolation in initial flight stage and maneuvering flight process two kinds of situations;
The pressure heart design objective of described guided missile comprises the guided missile pressure heart designing requirement of guided missile in initial flight stage and maneuvering flight process two kinds of situations after isolation.
Step 2, determines the contour structures not with rear guided missile; Be specially: according to the population parameter of the determined guided missile of step 1 and the pressure heart design objective of guided missile, design meets the contour structures not with rear guided missile that heart designing requirement pressed by guided missile in maneuvering flight process, and it comprises by determining that body 1 bus geometric parameter and rudder face geometric parameter determine guided missile profile; Wherein body 1 bus geometric parameter comprises body 1 maximum gauge, body 1 length and body 1 bus curvilinear equation; Described rudder face geometric parameter comprises the section shape of the chord length of rudder face, the length of rudder face and rudder face.
Step 3, increases by a rear 2 at the afterbody of missile airframe 1, and determines the contour structures being with rear guided missile; Be specially, the contour structures of band rear guided missile to meet in step 1 determine the population parameter of guided missile and the pressure heart design objective of guided missile.
The contour structures of described rear 2 is the tail skirt structure with angle of flare θ, and the diameter of ending place of this tail skirt structure is D2, the diameter of the section start of tail skirt structure is D1; The described angle of flare is θ, and θ >0 °; The diameter D2 of ending place of tail skirt structure is D2/D1 with the ratio of the diameter D1 of the section start of tail skirt structure, and D2/D1>1.0;
In the present embodiment, as shown in Figure 1, angle of flare θ=25 ° of tail skirt structure, the diameter D2 of ending place of tail skirt structure is D2/D1=1.5 with the ratio of the diameter D1 of the section start of tail skirt structure, and the diameter D1 of the section start of tail skirt structure is equal with the body 1 base diameter D not with rear guided missile determined in described step 2.
Step 4, determines the practical flight scheme of guided missile, is specially, and in the initial flight stage after guided missile is separated, now guided missile flies, for increasing the stability in guided missile initial flight stage with the configuration state of band rear guided missile determined in step 3;
When the guided missile initial flight stage terminates or end mobile needs to obtain high maneuver, under the effect of shedding separating mechanism, rear 2 from the portion of body 1 from, after this in maneuvering flight process, guided missile flies with the configuration state not with rear guided missile determined in step 2, make like this in maneuvering flight process, entirely to suppress heart reach, and ensure good maneuverability.
As shown in Figure 2, for different flight Mach number, by aerodynamic numerical simulation calculation band rear guided missile be not with rear guided missile after isolation in initial flight stage and maneuvering flight process two kinds of situations guided missile press down heart characteristic at Low Angle Of Attack, in Fig. 2, horizontal ordinate is Mach number Ma, and ordinate is for entirely to suppress heart XCP; Contrast from result of calculation, the design not with rear guided missile is compared in the design of employing band rear guided missile, guided missile entirely suppress the heart obviously after move, after under different Mach number, Low Angle Of Attack presses down the heart, the amount of moving all reaches 5%, after considering barycenter, the amount of moving is less, like this in the guided missile initial flight stage after isolation, the steady state stability of guided missile can obviously increase, and increases about 4.5%.
Adopt the present invention, the separable rear 2 in tail skirt structure is increased at missile tail, guided missile steady state stability in guided missile detachment process can be improved, more be conducive to stable separation, simultaneously when rear 2 is after body 1 separation, entirely suppress heart reach, when making maneuvering flight, guided missile steady state stability is unlikely excessive, ensure that good maneuverability.
The word in description orientation adopted herein " on ", D score, "left", "right" etc. are all convenience in order to illustrate based on the orientation in accompanying drawing shown in drawing, in actual device, these orientation may be different due to the disposing way of device.
In sum, embodiment of the present invention only provides a kind of embodiment of the best, technology contents of the present invention and technical characterstic disclose as above, but the personage being familiar with the technology still may do the various replacement and the modification that do not deviate from creation spirit of the present invention based on disclosed content; Therefore, protection scope of the present invention is not limited to the technology contents that embodiment discloses, therefore all equivalence changes done according to shape of the present invention, structure and principle, be all encompassed in protection scope of the present invention.
Claims (7)
1. the high-speed missile Exterior Surface Design for pressing the heart to regulate, is characterized in that comprising the steps:
Step 1, determines the population parameter of guided missile and the pressure heart design objective of guided missile;
Step 2, determines the contour structures not with rear guided missile;
Step 3, increases by a rear at the afterbody of missile airframe, and determines the contour structures being with rear guided missile.
2. a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate according to claim 1, it is characterized in that, preferably, described method also comprises:
Step 4, determines the practical flight scheme of guided missile, is specially, and in the initial flight stage after guided missile is separated, now guided missile flies, for increasing the stability in guided missile initial flight stage with the configuration state of band rear guided missile determined in step 3;
When the guided missile initial flight stage terminates or end mobile needs to obtain high maneuver, under the effect of shedding separating mechanism, rear from the portion of guided missile from, after this in maneuvering flight process, guided missile flies with the configuration state not with rear guided missile determined in step 2, makes so entirely to suppress heart reach in maneuvering flight process.
3. a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate according to claim 1, it is characterized in that, preferably, the population parameter of described guided missile comprises flight Mach number, height and the angle of attack of guided missile after isolation in initial flight stage and maneuvering flight process two kinds of situations;
The pressure heart design objective of described guided missile comprises the guided missile pressure heart designing requirement of guided missile in initial flight stage and maneuvering flight process two kinds of situations after isolation.
4. a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate according to claim 1, it is characterized in that, preferably, the contour structures not with rear guided missile is determined in described step 2, be specially: according to the population parameter of the determined guided missile of step 1 and the pressure heart design objective of guided missile, design meets the contour structures not with rear guided missile that heart designing requirement pressed by guided missile in maneuvering flight process, and it comprises by determining that body bus geometric parameter and rudder face geometric parameter determine guided missile profile; Wherein body bus geometric parameter comprises body maximum gauge, body length and body bus curvilinear equation; Described rudder face geometric parameter comprises the section shape of the chord length of rudder face, the length of rudder face and rudder face.
5. a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate according to claim 1, it is characterized in that, preferably, described step 3 is specially, increase by a rear at the afterbody of missile airframe, and determine the contour structures being with rear guided missile, the contour structures of this band rear guided missile to meet in step 1 determine the population parameter of guided missile and the pressure heart design objective of guided missile.
6. a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate according to claim 1, it is characterized in that, preferably, the contour structures of described rear is the tail skirt structure with angle of flare θ, and the diameter of ending place of this tail skirt structure is D2, the diameter of the section start of tail skirt structure is D1; The described angle of flare is θ, and θ >0 °; The diameter D2 of ending place of tail skirt structure is D2/D1 with the ratio of the diameter D1 of the section start of tail skirt structure, and D2/D1>1.0.
7. a kind of high-speed missile Exterior Surface Design for pressing the heart to regulate according to claim 6, is characterized in that, preferably, the diameter D1 of the section start of tail skirt structure is equal with the body base diameter D not with rear guided missile determined in described step 2.
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| CN201510065577.5A CN104598696B (en) | 2015-02-09 | 2015-02-09 | A kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105799949A (en) * | 2016-05-12 | 2016-07-27 | 上海微小卫星工程中心 | Pressure center design method, attitude control method and system of suborbital satellite |
| CN107891979A (en) * | 2017-09-28 | 2018-04-10 | 中国运载火箭技术研究院 | A kind of hypersonic aircraft can adjust tranquilizer |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107844643A (en) * | 2017-10-25 | 2018-03-27 | 北京电子工程总体研究所 | Guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation |
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| CA2670325C (en) * | 2006-11-30 | 2013-06-11 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
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| CA2670325C (en) * | 2006-11-30 | 2013-06-11 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
Non-Patent Citations (2)
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| 于云峰等: "无翼式推力矢量控制导弹总体设计方法研究——重心及压心规划", 《西北工业大学学报》 * |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799949A (en) * | 2016-05-12 | 2016-07-27 | 上海微小卫星工程中心 | Pressure center design method, attitude control method and system of suborbital satellite |
| CN105799949B (en) * | 2016-05-12 | 2018-05-15 | 上海微小卫星工程中心 | A kind of pressure heart design method, attitude control method and the system of Asia orbiter |
| CN107891979A (en) * | 2017-09-28 | 2018-04-10 | 中国运载火箭技术研究院 | A kind of hypersonic aircraft can adjust tranquilizer |
| CN107891979B (en) * | 2017-09-28 | 2019-10-18 | 中国运载火箭技术研究院 | A kind of adjustable tranquilizer of hypersonic aircraft |
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