CN104089546B - The variable aerodynamic arrangement structure of body - Google Patents
The variable aerodynamic arrangement structure of body Download PDFInfo
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- CN104089546B CN104089546B CN201410179325.0A CN201410179325A CN104089546B CN 104089546 B CN104089546 B CN 104089546B CN 201410179325 A CN201410179325 A CN 201410179325A CN 104089546 B CN104089546 B CN 104089546B
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Abstract
The invention discloses a kind of variable aerodynamic arrangement structure of body, be specifically related to a kind of body of taking into account in the change aerodynamic arrangement structure without control mission phase stability and correction stage accuracy at target.Adopt and become aerodynamic configuration scheme, the initial ballistic path of trajectory, empennage locking, in little empennage aerodynamic arrangement, can ensure that projectile flight is stablized, and can reduce again resistance and improve range; At terminal phase, empennage launches, and become large empennage aerodynamic arrangement, add the steady state stability of body, the body attitude angular oscillation energy Fast Convergent that impulsive force is caused, meets control system requirement.The present invention takes into account the advantage of fixing empennage aerodynamic arrangement and large empennage aerodynamic arrangement, the requirement of body steady state stability can be met, reducing impulsive force causes body attitude angular oscillation on the impact of control system, can ensure again range and revise required precision, repeatedly range test checking shows concept feasible.
Description
Technical field
The present invention relates to STT missile field, be specifically related to the variable aerodynamic arrangement structure of body.
Background technology
In modern war, utilize conventional military platform to develop the dexterous Missile Body processed of low cost, not only significantly can promote the fighting efficiency of conventional weapon, also can equip our troops in a large number, become one of developing direction of various countries' Missile Body.At present, along with the development of electronic technology, photoelectric technology, microprocessing and guidance technology, the miniaturization of guidance component and the progress of anti high overload ability, make the technical conditions of conventional body guidanceization more ripe, kind and the scale of Missile Body processed also progressively expand, and the effect that it plays in war is also more and more important.
Adopt the simple and easy correction body that pulsed motor controls, compel bullet with standard and compare, it effectively can improve fire accuracy, under identical operation condition, can reduce body consumption by a relatively large margin; Compare with the guided missile of precise guidance or terminal-guided shell, do not need steering gear control system, structure is simple, manufacture and maintenance cost relatively low, therefore can equip in a large number.But still there is following technological deficiency in existing body aerodynamic arrangement scheme:
(1) the pneumatic structure layout of conventional set body, fixing aerodynamic arrangement's scheme of empennage and the empennage of body is adopted to fix, fin area is less, resistance coefficient is little but cannot meet stability requirement, especially after the momentum effect of Trajectory-terminal pulsed motor, produces angle of attack amplitude larger, because body steady state stability is lower, angle of attack convergence is comparatively slow, cannot meet control system requirement, causes revising precision lower.
(2) according to the stability requirement of latter end correction section, the empennage devising large empennage aerodynamic arrangement scheme and body is larger, after pulsed motor momentum effect, because steady state stability improves, angle of attack converges faster, when next pulsed motor igniting, the angle of attack converges in control system permissible range, meets control overflow.But compared with fixing empennage aerodynamic arrangement, large empennage aerodynamic arrangement body resistance coefficient increases, and range reduces, and cannot meet the requirement of simple and easy correction body range.
Due to the existence of the problems referred to above, the present inventor furthers investigate existing body aerodynamic arrangement structure, to solve the problem that body correction precision is lower, range reduces.
Summary of the invention
In order to overcome the problems referred to above, present inventor has performed and study with keen determination, found that, by designing a kind of body that can change tail structure, namely the body structure that a kind of aerodynamic arrangement scheme is variable is designed, in projectile flight process, in suitable, change aerodynamic arrangement's structure of body, make body when the nothing control mission phase that trajectory is initial, empennage locks by sleeve, form the body structure of fixing empennage, now tail structure is less, can ensure that projectile flight is stablized, and can reduce again resistance and improve range; At the reaching advanced stages of ballistic flight, control sleeve by control device to move, empennage by sleeve is fixed is flicked, becomes large empennage, form large empennage aerodynamic arrangement, add the steady state stability of body, the body attitude angular oscillation energy Fast Convergent that impulsive force is caused, meets control system requirement, completes the control in the stage of projectile flight, accurately hit, thus complete the present invention.
Main purpose of the present invention is to provide following aspect:
(1) the variable aerodynamic arrangement structure of body, is characterized in that, afterbody 1 profile of this body is cylindric, has sleeve 2, the end of afterbody 1 is provided with fin holder 4, fin holder 4 is provided with fin 5 at afterbody overcoat,
Described sleeve is the tubular of both ends open, sleeve 2 is fixed on afterbody 1 by alignment pin 3, remove alignment pin 3, sleeve can slide on afterbody along elastomer axis direction, sleeve 2 barrel offers venthole 21, is namely provided with outwardly fin circle band 22 away from one end of bullet in sleeve rear end;
The stripe board that described fin 5 is made for metal material, multiple fin 5 is installed on around afterbody 1 equably, the direction, plate face of fin 5 and the cylinder of afterbody perpendicular, namely body axle center is positioned in the plane at place, plate face of fin, the mounting means of fin is: fin rear end is fixed on the fin holder 4 of body by bearing pin 6, fin front end is embedded in the fin circle band 22 on sleeve, is namely fixed on body by sleeve and bearing pin by fin;
The inside of afterbody 1 is provided with fiery device 7, fuel is placed in described fiery device 7, fiery device 7 is connected with breather pipe 8, and described breather pipe 8 is T-shaped, and the other two ends that breather pipe 8 is not connected with fiery device extend in the space between sleeve and afterbody 1;
Wherein, spring assembly is provided with in bearing pin outer cover, described spring assembly comprises torsionspring, during fin circle band 22 locking tabs, fin compressing turns torsion spring, makes torsionspring store power, when sleeve moves forward, when fin front end is deviate from fin circle band 22, torsionspring drives fin to rotate around bearing pin 6; After described rotation stops, the missile wing angle of sweep of fin is 55 ° ~ 65 °;
The nothing control mission phase that projectile flight process can be divided into trajectory initial and having of Trajectory-terminal control the correction stage;
Body when storing and trajectory initial without control mission phase time, sleeve fixed tab, body is the fixing body of empennage, and namely now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement;
Body in flight course, enter Trajectory-terminal have control the correction stage time, sleeve slides forward, fin flicks by spring assembly, and body is the body of large empennage, and namely now the aerodynamic arrangement of body is large empennage aerodynamic arrangement.
(2) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), it is characterized in that, body enter Trajectory-terminal have control the correction stage time, fiery device igniting, the high-temperature gas produced is delivered in the space between sleeve and afterbody 1 through breather pipe, fracture alignment pin 3 promote sleeve slides forward and namely slide towards extreme direction before body, and fin is deviate from fin circle band 22, and fin 5 is upspring.
(3) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), it is characterized in that, in projectile flight process, the time point in control correction stage that has entering Trajectory-terminal is journey ETL estimated time of loading, ground Combat Command System draws journey ETL estimated time of loading according to ballistic computation, and passing to body information attachment means, information is passed to armed body by body information attachment means.
(4) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), is characterized in that, when body is with the control correction stage and forms large empennage body structure, missile wing angle of sweep is 60 °.
(5) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), is characterized in that, the established angle scope that fin plays axle is relatively 2 ° ~ 3 °, to ensure body rotating speed to control within the scope of 5 ~ 10 turns/s.
(6) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), it is characterized in that, be provided with the board slot 41 stretched into for fin 5 in the middle part of fin holder 4, fin holder 4 and fin (5) connect as one through the through hole on board slot and fin 5 by bearing pin 6.
(7) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), is characterized in that, fin 5 shares six, the setting of 60 °, each fin interval.
(8) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), is characterized in that, the diameter that afterbody 1 is positioned at the part of sleeve is less than the diameter of other parts of afterbody 1.
(9) the variable aerodynamic arrangement structure of the body according to above-mentioned (1), it is characterized in that, alignment pin 3 has two, and alignment pin 3 is made up of aluminum material, is easy to fracture.
Aerodynamic arrangement of the present invention scheme takes into account the advantage of fixing empennage aerodynamic arrangement and large empennage aerodynamic arrangement, upspringing dexterously by empennage, change aerodynamic arrangement's structure, thus the requirement of body steady state stability can be met, reducing impulsive force causes body attitude angular oscillation to affect control system, can ensure again range and revise required precision.
Accompanying drawing explanation
Fig. 1 illustrates the fixing empennage body structure schematic diagram fixed by sleeve according to the fin of the variable aerodynamic arrangement structure of a kind of preferred embodiment of the present invention body;
Fig. 2 illustrates the large empennage body structure schematic diagram of upspringing according to the fin of the variable aerodynamic arrangement structure of a kind of preferred embodiment of the present invention body;
Fig. 3 illustrates the structural representation amplified according to the afterbody of the variable aerodynamic arrangement structure of a kind of preferred embodiment of the present invention body;
Fig. 4 illustrates the afterbody broken section structural representation of the variable aerodynamic arrangement structure according to a kind of preferred embodiment of the present invention body;
Fig. 5 illustrates the sleeve restriction tab construction schematic diagram according to the variable aerodynamic arrangement structure of a kind of preferred embodiment of the present invention body
Fig. 6 illustrates the fixing empennage aerodynamic arrangement drag-coefficient curve of the variable aerodynamic arrangement structure according to a kind of preferred embodiment of the present invention body;
Fig. 7 illustrates large empennage aerodynamic arrangement drag-coefficient curve;
Fig. 8 illustrates the large empennage aerodynamic arrangement body angle of attack simulation curve of the variable aerodynamic arrangement structure according to a kind of preferred embodiment of the present invention body;
Fig. 9 illustrates the large empennage aerodynamic arrangement flight test identification angle of attack curve of the variable aerodynamic arrangement structure according to a kind of preferred embodiment of the present invention body.
Drawing reference numeral illustrates:
1-afterbody
2-sleeve
3-alignment pin
4-fin holder
5-fin
6-bearing pin
7-prevails device
8-breather pipe
21-gas outlet
22-fin circle band
41-board slot
Detailed description of the invention
Below by the present invention is described in detail, the features and advantages of the invention will illustrate along with these and become more clear, clear and definite.
Word " exemplary " special here means " as example, embodiment or illustrative ".Here need not be interpreted as being better than or being better than other embodiment as any embodiment illustrated by " exemplary ".Although the various aspects of embodiment shown in the drawings, unless otherwise indicated, accompanying drawing need not be drawn in proportion.
Front end in the present invention refers to the direction that guided missile head points to, and rear end is relative with front end, and front end and rear end are the both directions along elastomer axis, and can find out that from Fig. 1 and Fig. 2 described front end refers to the left side in figure, rear end refers to the right side in figure.
In a kind of preferred embodiment of the variable aerodynamic arrangement structure according to body provided by the invention, as shown in the figures 1 and 2, afterbody 1 profile of this body is cylindric, has sleeve 2, the end of afterbody is provided with fin holder 4 at afterbody overcoat, fin holder is provided with fin 5, wherein, jacket casing is in the centre position of afterbody, and fin holder is then positioned at the least significant end of afterbody, sleeve and, leave certain gap between fin holder.
In one preferred embodiment, as shown in Figure 1, Figure 2, shown in Fig. 3 and Fig. 4, sleeve is the tubular of both ends open, sleeve is fixed on afterbody by alignment pin 3, remove alignment pin, sleeve can slide on afterbody along elastomer axis direction, and sleeve wall offers venthole 21, is namely provided with outwardly fin circle band 22 away from one end of bullet in sleeve rear end; Wherein, sleeve along elastomer axis direction forward slip, fin circle band be sleeve afterbody outwardly become, one-body molded with sleeve, its diameter is large compared with sleeve, for fixing or restriction fin.
In one preferred embodiment, as shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4 and Fig. 5, the stripe board that fin 5 is made for metal material, multiple fin 5 is installed on around afterbody equably, the direction, plate face of fin and the cylinder of afterbody perpendicular, namely body axle center is positioned in the plane at place, plate face of fin, the mounting means of fin is: fin rear end is fixed on the fin holder of body by bearing pin 6, fin front end is embedded in the fin circle band 22 on sleeve, is namely fixed on body by sleeve and bearing pin by fin; Wherein, fin number preferably selects 6, the setting of 60 °, each fin interval, and fin front end is tiny compared with rear end, is convenient to extend in fin circle band 22, if motionless in fin circle band 22, fin is fixed firmly, can not move.
In one preferred embodiment, as Fig. 1, Fig. 2, shown in Fig. 3 and Fig. 4, the inside of afterbody 1 is provided with fiery device 7, fuel is placed in described fiery device, fiery device 7 is connected with breather pipe 8, described breather pipe 8 is T-shaped, the other two ends that breather pipe 8 is not connected with fiery device extend in the space between sleeve and afterbody 1, to fracture alignment pin owing to needing the pressure produced by high-temperature gas, the power needed is larger, generally two of breather pipe outlet sides are placed on the nearer position of Distance positioning pin, convenient to break alignment pin in the shortest time infolding, promote sleeve slides forward.
The power selecting fiery device to produce in the present invention is opened to control empennage fin, and this mode stable performance, reliability is high.
In one preferred embodiment, as shown in Figure 1, Figure 2, spring assembly is provided with in bearing pin outer cover shown in Fig. 3 and Fig. 5, described spring assembly comprises torsionspring, during fin circle band 22 locking tabs, fin compressing turns torsion spring, makes torsionspring store power, when sleeve moves forward, when fin front end is deviate from fin circle band 22, torsionspring drives fin to rotate around bearing pin 6; After described rotation stops, the missile wing angle of sweep of fin is 55 ° ~ 65 °, the preferred missile wing angle of sweep selecting 60 ° in the present invention.
In one preferred embodiment, the nothing that projectile flight process can be divided into trajectory initial controls mission phase and having of Trajectory-terminal controls the correction stage; In projectile flight process, the control time point that opens in control correction stage is had to be journey ETL estimated time of loading, launch front ground Combat Command System and draw journey ETL estimated time of loading by ballistic computation, body information attachment means is passed to by cable, information is bound to armed body by attachment means, journey ETL estimated time of loading and ballistic flight distance, flight time and when launching, body parameter is as the angle of departure, initial velocity etc. are relevant.
Body when storing and trajectory initial without control mission phase time, lock tube fixed tab, body is the fixing body of empennage, and namely now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement,
Body in flight course, enter Trajectory-terminal have control the correction stage time, lock tube is opened, and fin flicks by spring assembly, and body is the body of large empennage, and namely now the aerodynamic arrangement of body is large empennage aerodynamic arrangement.
The control device of body is according to the instruction pre-set in one preferred embodiment, body enter Trajectory-terminal have control the correction stage time, fiery device igniting, the high-temperature gas produced is delivered in the space between sleeve and afterbody through breather pipe, fracture alignment pin promote sleeve slides forward and namely slide towards extreme direction before body, fin is deviate from fin circle band, and fin is upspring and produced high-temperature gas drive sleeve slides forward, and then fin is upspring.
In further preferred embodiment, according to the distance relative to target before body is launched, determine the time be in after body is launched without control mission phase, and at the end of nothing control mission phase, send the instruction preset, launched by control device fin, body is with the control correction stage.Control instruction in the present invention is stored by the computer system of body inside and is sent to control device in predetermined time.
In one preferred embodiment, fin can make various ways, as long as be satisfied with when being with the control correction stage, fin can be upspring, change aerodynamic arrangement's structure of body, such as, can change angle of sweep when body is fixed, the length of change fin and thickness etc.
In one preferred embodiment, the established angle scope that fin plays axle is relatively 2 ~ 3 °, to ensure body rotating speed to control within the scope of 5 ~ 10 turns/s.
In one preferred embodiment, before fin is upspring, by compression, when sleeve unclamps fin, spring assembly drives fin to upspring to spring assembly, reaches the extreme position that fin is upspring; Spring assembly in the present invention can be arranged on bearing pin, and namely the major part of spring assembly is torsionspring, and torsionspring is enclosed within bearing pin; Spring assembly also can be arranged between fin and body, and namely the major part of spring assembly is Compress Spring, and during storage, Compress Spring is compressed between fin and body; Spring assembly also can be arranged on fin rear, and namely the major part of spring assembly is extension spring, and be stretched during extension spring storage, when lock tube unclamps, extension spring pulls fin to rotate, and preferably selects torsionspring in the present invention.
In one preferred embodiment, be provided with the board slot 41 stretched into for fin in the middle part of fin holder, fin holder and fin connect as one through the through hole on board slot and fin by bearing pin.
In one preferred embodiment, the diameter that afterbody 1 is positioned at the part of sleeve is less than the diameter of other parts of afterbody, to make the space between sleeve and afterbody larger.
In one preferred embodiment, alignment pin 3 shares two, and two alignment pins are symmetrical arranged, and alignment pin 3 is made up of aluminum material, are easy to fracture.
In the present invention, when the nothing control mission phase that trajectory is initial, fin locks, now body is aerodynamic arrangement's body of fixing empennage, body steady state stability is 15%, and with the angle of attack and Mach number change curve as shown in Figure 6, and the resistance coefficient of mutually isostructural large empennage aerodynamic arrangement body with the angle of attack and Mach number change curve as shown in Figure 7 for resistance coefficient, can find out that fixing empennage aerodynamic arrangement without the employing of control mission phase can ensure that projectile flight is stablized, and can reduce again resistance and improve range; Described mutually isostructural large empennage aerodynamic arrangement body refers to that the overall structure of this body is compared with aerodynamic arrangement's body of above-mentioned fixing empennage, and only have tail structure different, other structures are identical.
In the present invention, Trajectory-terminal have control the correction stage time, fin launches, body becomes the body of large empennage aerodynamic arrangement, body six degrees of freedom model is utilized to emulate, adopt large empennage aerodynamic arrangement have control bullet revise the stage angle of attack simulation curve as shown in Figure 8, as can be seen from the figure: after the effect of single pulse power, produce the angle of attack less; Because steady state stability improves, angle of attack converges faster, when the igniting of next pulsed motor, the angle of attack converges in control system permissible range, namely within 2 °, meets control overflow.
By playing test flight data identification to having to control, obtain adopting having of large empennage aerodynamic arrangement to control the flight test identification angle of attack curve of body in the stage of correction, as shown in Figure 9, the body of fixing empennage aerodynamic arrangement cannot meet steady state stability needed for endgame correction and dynamic characteristic parameter; According to the control overflow having the control correction stage, calculated by Control System Imitation, body steady state stability should be greater than 30%, and large empennage aerodynamic arrangement adds the steady state stability of body, and steady state stability is about 35%.Mathematical simulation and test flight data identification result absolutely prove and adopt the body of large empennage aerodynamic arrangement can meet control overflow in the control correction stage.
Aerodynamic arrangement described in the present invention refers to tail fin design position or the form of body, and aerodynamic arrangement is variable refers to the tail fin design form that can change body; The angle of attack refers to the angle between the projection of velocity V on longitudinal plane of symmetry and the guided missile longitudinal axis; Body steady state stability refers to the distance of body aerodynamic center to center of gravity and the ratio of bullet length, and general aerodynamic center steady state stability after center of gravity is just; Mach number refers to the speed of certain point and the ratio of the local velocity of sound of this point in flow field.
More than in conjunction with detailed description of the invention and exemplary example to invention has been detailed description, but these explanations can not be interpreted as limitation of the present invention.It will be appreciated by those skilled in the art that when not departing from spirit and scope of the invention, can carry out multiple equivalencing, modification or improvement to technical solution of the present invention and embodiment thereof, these all fall within the scope of the present invention.Protection scope of the present invention is as the criterion with claims.
Claims (9)
1. the variable aerodynamic arrangement structure of body, it is characterized in that, afterbody (1) profile of this body is cylindric, sleeve (2) is had at afterbody overcoat, the end of afterbody (1) is provided with fin holder (4), fin holder (4) is provided with fin (5)
Described sleeve is the tubular of both ends open, sleeve (2) is fixed on afterbody (1) by alignment pin (3), remove alignment pin (3), sleeve can slide on afterbody along elastomer axis direction, sleeve (2) barrel offers venthole (21), is namely provided with outwardly fin circle band (22) away from one end of bullet in sleeve rear end;
The stripe board that described fin (5) is made for metal material, multiple fin (5) is installed on afterbody (1) around equably, the direction, plate face of fin (5) and the cylinder of afterbody perpendicular, namely body axle center is positioned in the plane at place, plate face of fin, the mounting means of fin is: fin rear end is fixed on the fin holder (4) of body by bearing pin (6), fin front end is embedded in the fin circle band (22) on sleeve, is namely fixed on body by sleeve and bearing pin by fin;
The inside of afterbody (1) is provided with fiery device (7), fuel is placed in described fiery device (7), fiery device (7) is connected with breather pipe (8), described breather pipe (8) is T-shaped, and the other two ends that breather pipe (8) is not connected with fiery device extend in the space between sleeve and afterbody (1);
Wherein, spring assembly is provided with in bearing pin outer cover, described spring assembly comprises torsionspring, during fin circle band (22) locking tabs, fin compressing turns torsion spring, makes torsionspring store power, when sleeve moves forward, when fin front end is deviate from fin circle band (22), torsionspring drives fin to rotate around bearing pin (6); After described rotation stops, the missile wing angle of sweep of fin is 55 ° ~ 65 °;
The nothing control mission phase that projectile flight process can be divided into trajectory initial and having of Trajectory-terminal control the correction stage;
Body when storing and trajectory initial without control mission phase time, sleeve fixed tab, body is the fixing body of empennage, and namely now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement;
Body in flight course, enter Trajectory-terminal have control the correction stage time, sleeve slides forward, fin flicks by spring assembly, and body is the body of large empennage, and namely now the aerodynamic arrangement of body is large empennage aerodynamic arrangement.
2. the variable aerodynamic arrangement structure of body according to claim 1, it is characterized in that, body enter Trajectory-terminal have control the correction stage time, fiery device igniting, the high-temperature gas produced is delivered in the space between sleeve and afterbody (1) through breather pipe, fracture alignment pin (3) promote sleeve slides forward and namely slide towards extreme direction before body, and fin is deviate from fin circle band (22), and fin (5) is upspring.
3. the variable aerodynamic arrangement structure of body according to claim 1, it is characterized in that, in projectile flight process, the time point in control correction stage that has entering Trajectory-terminal is journey ETL estimated time of loading, ground Combat Command System draws journey ETL estimated time of loading according to ballistic computation, and passing to body information attachment means, information is passed to armed body by body information attachment means.
4. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, when body is with the control correction stage and forms large empennage body structure, missile wing angle of sweep is 60 °.
5. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, the established angle scope that fin plays axle is relatively 2 ° ~ 3 °, to ensure body rotating speed to control within the scope of 5 ~ 10 turns/s.
6. the variable aerodynamic arrangement structure of body according to claim 1, it is characterized in that, fin holder (4) middle part is provided with the board slot (41) stretched into for fin (5), and fin holder (4) and fin (5) connect as one through the through hole on board slot and fin (5) by bearing pin (6).
7. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, fin (5) shares six, the setting of 60 °, each fin interval.
8. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, the diameter that afterbody (1) is positioned at the part of sleeve is less than the diameter of afterbody (1) other parts.
9. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, alignment pin (3) has two, and alignment pin (3) is made up of aluminum material, is easy to fracture.
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| CN105865271B (en) * | 2016-05-27 | 2017-09-05 | 中国人民解放军国防科学技术大学 | A kind of portable missile of use fast aeration missile wing |
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| CN109472073B (en) * | 2018-10-30 | 2023-03-31 | 中国运载火箭技术研究院 | Aircraft pneumatic layout adjusting method and device and electronic equipment |
| CN109823515B (en) * | 2019-01-24 | 2020-12-15 | 北京理工大学 | Spoiler system arranged on guided aircraft and method for applying spoiler system |
| CN110525633B (en) * | 2019-08-06 | 2020-12-15 | 上海机电工程研究所 | Stabilizer for aircraft |
| CN110657716A (en) * | 2019-09-26 | 2020-01-07 | 南京航空航天大学 | Aircraft telescopic wing panel control device |
| CN111486755B (en) * | 2020-03-24 | 2021-01-26 | 北京理工大学 | Falling speed control method of variable pneumatic profile guidance equipment |
| CN112414230A (en) * | 2020-10-15 | 2021-02-26 | 安徽神剑科技股份有限公司 | Throwing bomb for rescue |
| CN112660427B (en) * | 2020-11-30 | 2023-01-31 | 上海航天控制技术研究所 | Deep space exploration separation monitoring satellite unlocking device |
| CN114036651B (en) * | 2022-01-11 | 2022-03-25 | 中国空气动力研究与发展中心计算空气动力研究所 | Low-resistance minor-caliber rotating body bullet body and design method |
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