CN104089546A - Variable pneumatic layout structure for projectile body - Google Patents
Variable pneumatic layout structure for projectile body Download PDFInfo
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- CN104089546A CN104089546A CN201410179325.0A CN201410179325A CN104089546A CN 104089546 A CN104089546 A CN 104089546A CN 201410179325 A CN201410179325 A CN 201410179325A CN 104089546 A CN104089546 A CN 104089546A
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Abstract
The invention discloses a variable pneumatic layout structure for a projectile body, and particularly relates to a variable pneumatic layout structure capable of combining the stability of the projectile body in a free flight stage and the hitting accuracy of the projectile body in a correction stage. A variable pneumatic shape scheme is adopted; an empennage is locked into a small-empennage pneumatic layout in an original free flight section of a trajectory, so that the flight stability of the projectile body can be ensured, resistance can be reduced, and the range can be prolonged; in a tail section of the trajectory, the empennage is unfolded into a large-empennage pneumatic layout, so that the static stability of the projectile body is improved, projectile body attitude angle oscillation caused by surging force can be rapidly converged, and the requirements of a control system can be met. According to the variable pneumatic layout structure for the projectile body, the advantages of a fixed-empennage pneumatic layout and the large-empennage pneumatic layout are combined, so that a requirement on the static stability of the projectile body can be met, the influence of the projectile body attitude angle oscillation caused by surging force on the control system can be reduced, the range can be ensured, and a requirement on the correction accuracy can also be met; multiple range tests show that the scheme is feasible.
Description
Technical field
The present invention relates to guided missile control field, be specifically related to the variable aerodynamic arrangement structure of body.
Background technology
In modern war, utilize the dexterous Missile Body processed of conventional military platform development low cost, not only can significantly 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 processed.At present, along with the development of electronic technology, photoelectric technology, microprocessing and guidance technology, the progress of the miniaturization of guidance component and anti high overload ability, make the technical conditions of conventional body guidanceization more ripe, the kind of Missile Body processed and scale also progressively expand, and the effect that it brings into play in war is also more and more important.
Adopt the simple and easy correction body of pulsed motor control, compel bullet compare with standard, it can effectively improve fire accuracy, under identical operation condition, can reduce by a relatively large margin body consumption; Guided missile or terminal-guided shell with precise guidance are compared, and do not need steering gear control system, simple in structure, and manufacture and maintenance cost are 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, the aerodynamic arrangement's scheme that adopts fixing empennage is that the empennage of body is fixed, 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 slower, cannot meet control system requirement, causes revising precision lower.
(2) according to the stability requirement of latter end correction section, design Liao great empennage aerodynamic arrangement scheme is that the empennage of body is larger, after pulsed motor momentum effect, because steady state stability improves, angle of attack converges faster, in the time of next pulsed motor igniting, the angle of attack converges in control system permissible range, meets and controls requirement.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 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, the inventor has carried out research with keen determination, found that, by designing a kind of body that can change tail structure, design the variable body structure of a kind of aerodynamic arrangement scheme, in body flight course, in suitable, change aerodynamic arrangement's structure of body, make body trajectory initial without control mission phase time, sleeve locks empennage, form the body structure of fixing empennage, now tail structure is less, can ensure body flight stability, can reduce again resistance and improve range; In the stage in latter stage of ballistic flight, moved by control device control sleeve, the empennage of being fixed by sleeve is flicked, become large empennage, form large empennage aerodynamic arrangement, increase the steady state stability of body, the body attitude angle oscillation energy Fast Convergent that impulsive force is caused, meets control system requirement, completes the control in the stage of body flight, accurately hit, thus the present invention completed.
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 at afterbody overcoat, is provided with fin holder 4 at the end of afterbody 1, and fin 5 is installed on fin holder 4,
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 along elastomer axis direction on afterbody, on sleeve 2 barrels, offer venthole 21, be 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 fins 5 are installed on around afterbody 1 equably, the plate face direction of fin 5 and the cylinder of afterbody are perpendicular, be that body axle center is positioned in the plane at plate face place of fin, the mounting means of fin is: fin rear end is fixed on by bearing pin 6 on the fin holder 4 of body, fin front end is embedded in the fin circle band 22 on sleeve, by sleeve and bearing pin, fin is fixed on body;
Be provided with fiery device 7 in the inside of afterbody 1, the interior placement fuel of described fiery device 7, on fiery device 7, be connected with breather pipe 8, described breather pipe 8 is T-shaped, and the other two ends that breather pipe 8 is not connected in fiery device extend in the space between sleeve and afterbody 1;
Wherein, be provided with spring assembly in bearing pin outer cover, described spring assembly comprises torsionspring, when fin circle band 22 is locked fin, fin compressing turns torsion spring, makes torsionspring hold power, when sleeve moves forward, fin front end is when deviating from fin circle band 22, and torsionspring drives fin to rotate around bearing pin 6; After described rotation stops, the missile wing angle of sweep of fin is 55 °～65 °;
Body flight course can be divided into the initial correction stage of control that has without control mission phase and Trajectory-terminal of trajectory;
Body when storage and trajectory initial without control mission phase time, sleeve fixed tab, body is the fixing body of empennage, now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement;
Body is in flight course, and what enter Trajectory-terminal has control when the correction stage, and sleeve is to front slide, and spring assembly flicks fin, the body that body is large empennage, and now the aerodynamic arrangement of body is large empennage aerodynamic arrangement.
(2) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it is characterized in that, what enter Trajectory-terminal at body has control when the correction stage, fiery device igniting, the high-temperature gas producing is delivered in the space between sleeve and afterbody 1 through breather pipe, fracture alignment pin 3 promote sleeve and slide forward and to slide towards extreme direction before body, fin is deviate from fin circle band 22, and fin 5 is upspring.
(3) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it is characterized in that, in body flight course, the time point that has the control correction stage that enters Trajectory-terminal is journey ETL estimated time of loading, ground accuses that system calculates journey ETL estimated time of loading according to trajectory, and passing to body information attachment means, information is passed to armed body by body information attachment means.
(4) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it is characterized in that, when body has entered the control correction stage and formed large empennage body structure, missile wing angle of sweep is 60 °.
(5) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it is characterized in that, the established angle scope that fin plays axle is relatively 2 °～3 °, body rotating speed is controlled within the scope of 5～10 turn/s ensureing.
(6) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it is characterized in that, fin holder 4 middle parts are provided with the board slot 41 stretching into for fin 5, and bearing pin 6 connects as one fin holder 4 and fin (5) through the through hole on board slot and fin 5.
(7) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it is characterized in that, fin 5 shares six, the setting of 60 °, each fin interval.
(8) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, it 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) according to the variable aerodynamic arrangement structure of the body above-mentioned (1) Suo Shu, 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 is taken into account the advantage of fixing empennage aerodynamic arrangement and large empennage aerodynamic arrangement, upspringing by empennage dexterously, change aerodynamic arrangement's structure, thereby can meet the requirement of body steady state stability, reduce impulsive force and cause that the vibration of body attitude angle is on control system impact, can ensure again range and revise required precision.
Brief description of the drawings
Fig. 1 illustrates the fixing empennage body structure schematic diagram that the fin of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention is fixed by sleeve;
Fig. 2 illustrates the large empennage body structure schematic diagram that the fin of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention is upspring;
Fig. 3 illustrates the structural representation that the afterbody of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention amplifies;
Fig. 4 illustrates the afterbody broken section structural representation of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention;
Fig. 5 illustrates the sleeve restriction tab configurations schematic diagram of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention
Fig. 6 illustrates the fixing empennage aerodynamic arrangement drag-coefficient curve of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention;
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 of a kind of preferred embodiment body according to the present invention;
Fig. 9 illustrates the large empennage aerodynamic arrangement flight test identification angle of attack curve of the variable aerodynamic arrangement structure of a kind of preferred embodiment body according to the present invention.
Drawing reference numeral explanation:
1-afterbody
2-sleeve
3-alignment pin
4-fin holder
5-fin
6-bearing pin
The 7-device that prevails
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 become more clear, clear and definite along with these explanations.
Here special word " exemplary " means " as example, embodiment or illustrative ".Here needn't be interpreted as being better than or being better than other embodiment as " exemplary " illustrated any embodiment.Although the various aspects of embodiment shown in the drawings, unless otherwise indicated, needn't draw accompanying drawing 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, can find out that described front end refers to the left side in figure from Fig. 1 and Fig. 2, and rear end refers to the right side in figure.
According in a kind of preferred embodiment of the variable aerodynamic arrangement structure of body provided by the invention, as shown in Fig. 1 or 2, afterbody 1 profile of this body is cylindric, has sleeve 2 at afterbody overcoat, is provided with fin holder 4 at the end of afterbody, fin 5 is installed on fin holder, wherein, jacket casing is in the centre position of afterbody, and fin holder is positioned at the least significant end of afterbody, sleeve and, between fin holder, leave certain gap.
One preferred embodiment in, 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 along elastomer axis direction on afterbody, offers venthole 21 on sleeve wall, is provided with outwardly fin circle band 22 away from one end of bullet in sleeve rear end; Wherein, sleeve is along elastomer axis direction to front slide, and to be that sleeve afterbody is outwardly become fin circle band, and one-body molded with sleeve, its diameter is large compared with sleeve, for fixing or restriction fin.
One preferred embodiment in, 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 fins 5 are installed on around afterbody equably, the plate face direction of fin and the cylinder of afterbody are perpendicular, be that body axle center is positioned in the plane at plate face place of fin, the mounting means of fin is: fin rear end is fixed on by bearing pin 6 on the fin holder of body, fin front end is embedded in the fin circle band 22 on sleeve, by sleeve and bearing pin, fin is fixed on body; Wherein, fin number is preferably selected 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 fin circle band 22 is interior motionless, fin is fixed firmly, can not move.
One preferred embodiment in, as Fig. 1, Fig. 2, shown in Fig. 3 and Fig. 4, be provided with fiery device 7 in the inside of afterbody 1, in described fiery device, place fuel, on fiery device 7, be connected with breather pipe 8, described breather pipe 8 is T-shaped, the other two ends that breather pipe 8 is not connected in fiery device extend in the space between sleeve and afterbody 1, due to the pressure that need to produce by the high-temperature gas alignment pin that fractures, the power needing is larger, generally two outlet sides of breather pipe are placed on to the position nearer apart from alignment pin, convenient at the disconnected alignment pin of the shortest time infolding, promoting sleeve slides forward.
The power of selecting fiery device to produce in the present invention is controlled empennage fin and is opened, this mode stable performance, and reliability is high.
One preferred embodiment in, as shown in Figure 1, Figure 2, shown in Fig. 3 and Fig. 5, be provided with spring assembly in bearing pin outer cover, described spring assembly comprises torsionspring, when fin circle band 22 is locked fin, fin compressing turns torsion spring, makes torsionspring hold power, when sleeve moves forward, fin front end is when deviating from fin circle band 22, and 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 of selecting 60 ° in the present invention.
One preferred embodiment in, body flight course can be divided into trajectory initial have a control correction stage without control mission phase and Trajectory-terminal; In body flight course, there is the control time point that opens in control correction stage to be journey ETL estimated time of loading, launch front ground and accuse that system calculates journey ETL estimated time of loading by trajectory, pass to body information attachment means by cable, attachment means binds information to armed body, when journey ETL estimated time of loading and ballistic flight distance, flight time and transmitting, body parameter is as the angle of departure, and initial velocity etc. are relevant.
Body when storage and trajectory initial without control mission phase time, lock tube fixed tab, body is the fixing body of empennage, now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement,
Body is in flight course, and what enter Trajectory-terminal has control when the correction stage, and lock tube is opened, and spring assembly flicks fin, the body that body is large empennage, and now the aerodynamic arrangement of body is large empennage aerodynamic arrangement.
One preferred embodiment in the control device of body according to the instruction that pre-sets, what enter Trajectory-terminal at body has control when the correction stage, fiery device igniting, the high-temperature gas producing is delivered in the space between sleeve and afterbody through breather pipe, alignment pin promote sleeve and slide forward and to slide towards extreme direction before body fractures, fin is deviate from fin circle band, and fin is upspring and produced high-temperature gas band moving sleeve and slide forward, and then fin is upspring.
In further preferred embodiment, before body transmitting, according to the distance with respect to target, determine after body transmitting in the time without controlling mission phase, and in the time finishing without control mission phase, send the instruction presetting, launch by control device fin, body has entered the control correction stage.Control instruction in the present invention is stored and is sent to control device in predetermined time by the computer system of body inside.
One preferred embodiment in, fin can be made various ways, as long as be satisfied with having entered control when the correction stage, fin can be upspring, change aerodynamic arrangement's structure of body, for example, can change the angle of sweep of body when fixing, length and the thickness etc. of change fin.
One preferred embodiment in, the established angle scope that fin plays axle is relatively 2～3 °, body rotating speed is controlled within the scope of 5～10 turn/s ensureing.
One preferred embodiment in, before fin is upspring, spring assembly by compression, when sleeve unclamps fin, spring assembly drive fin upspring, reach the extreme position that fin is upspring; Spring assembly in the present invention can be arranged on bearing pin, and the major part of spring assembly is torsionspring, and torsionspring is enclosed within on bearing pin; Spring assembly also can be arranged between fin and body, and the major part of spring assembly is Compress Spring, and when storage, Compress Spring is compressed between fin and body; Spring assembly also can be arranged on fin rear, and the major part of spring assembly is extension spring, when extension spring storage, is stretched, and when lock tube unclamps, extension spring pulls fin rotation, preferably selects torsionspring in the present invention.
One preferred embodiment in, fin holder middle part is provided with the board slot 41 stretching into for fin, bearing pin connects as one fin holder and fin through the through hole on board slot and fin.
One preferred embodiment in, 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.
One preferred embodiment in, alignment pin 3 shares two, two alignment pins are symmetrical arranged, alignment pin 3 is made up of aluminum material, is easy to fracture.
In the present invention, trajectory initial without control when mission phase, fin locking, 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 the large empennage aerodynamic arrangement body of same structure with the angle of attack and Mach number change curve as shown in Figure 7 for resistance coefficient, can find out without the fixing empennage of control mission phase employing aerodynamic arrangement and can ensure body flight stability, can reduce again resistance and improve range; The large empennage aerodynamic arrangement body of described same structure refers to compared with the overall structure of this body and aerodynamic arrangement's body of above-mentioned fixing empennage, and only have tail structure difference, other structures are identical.
In the present invention, there is control when the correction stage at Trajectory-terminal, fin launches, body becomes the body of large empennage aerodynamic arrangement, utilize body six degrees of freedom model to carry out emulation, what adopt large empennage aerodynamic arrangement has control bullet at the angle of attack simulation curve in the stage of correction 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, in the time of the igniting of next pulsed motor, the angle of attack converges in control system permissible range, in 2 °, meets and controls requirement.
By playing test flight data identification to having to control, what obtain adopting large empennage aerodynamic arrangement has the flight test identification angle of attack curve of control body in the stage of correction, as shown in Figure 9, the body of fixing empennage aerodynamic arrangement cannot meet the required steady state stability of end correction and dynamic characteristic parameter; According to the control requirement that has the control correction stage, calculate by Control System Imitation, body steady state stability should be greater than 30%, and empennage aerodynamic arrangement has increased the steady state stability of body greatly, and steady state stability is about 35%.Mathematical simulation and test flight data identification result absolutely prove that the body of the large empennage of employing aerodynamic arrangement can meet control requirement in the control correction stage.
Aerodynamic arrangement described in the present invention refers to tail fin design position or the form of body, the variable tail fin design form that can change body that refers to of aerodynamic arrangement; The angle of attack refers to the projection of velocity V on the longitudinal plane of symmetry and the angle between the guided missile longitudinal axis; Body steady state stability refers to that body aerodynamic center is to the distance of center of gravity and the long ratio of bullet, general aerodynamic center after center of gravity steady state stability for just; Mach number refers to the ratio of the speed of certain point in flow field and the local velocity of sound of this point.
In conjunction with detailed description of the invention and exemplary example, the present invention is had been described in detail above, but these explanations can not be interpreted as limitation of the present invention.It will be appreciated by those skilled in the art that in the situation that not departing from spirit and scope of the invention, can carry out multiple replacement of equal value, modify or improve 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, there is sleeve (2) at afterbody overcoat, be provided with fin holder (4) at the end of afterbody (1), fin (5) is installed on fin holder (4)
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 along elastomer axis direction on afterbody, on sleeve (2) barrel, offer venthole (21), be 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 fins (5) are installed on afterbody (1) around equably, the plate face direction of fin (5) and the cylinder of afterbody are perpendicular, be that body axle center is positioned in the plane at plate face place of fin, the mounting means of fin is: fin rear end is fixed on by bearing pin (6) on the fin holder (4) of body, fin front end is embedded in the fin circle band (22) on sleeve, by sleeve and bearing pin, fin is fixed on body;
Be provided with fiery device (7) in the inside of afterbody (1), in described fiery device (7), place fuel, on fiery device (7), be connected with breather pipe (8), described breather pipe (8) is T-shaped, and the other two ends that breather pipe (8) is not connected in fiery device extend in the space between sleeve and afterbody (1);
Wherein, be provided with spring assembly in bearing pin outer cover, described spring assembly comprises torsionspring, when fin circle band (22) locking fin, fin compressing turns torsion spring, makes torsionspring hold power, when sleeve moves forward, fin front end is when deviating from fin circle band (22), and torsionspring drives fin to rotate around bearing pin (6); After described rotation stops, the missile wing angle of sweep of fin is 55 °～65 °;
Body flight course can be divided into the initial correction stage of control that has without control mission phase and Trajectory-terminal of trajectory;
Body when storage and trajectory initial without control mission phase time, sleeve fixed tab, body is the fixing body of empennage, now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement;
Body is in flight course, and what enter Trajectory-terminal has control when the correction stage, and sleeve is to front slide, and spring assembly flicks fin, the body that body is large empennage, and 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, what enter Trajectory-terminal at body has control when the correction stage, fiery device igniting, the high-temperature gas producing is delivered in the space between sleeve and afterbody (1) through breather pipe, fracture alignment pin (3) promote sleeve and slide forward and to slide towards extreme direction before body, 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 body flight course, the time point that has the control correction stage that enters Trajectory-terminal is journey ETL estimated time of loading, ground accuses that system calculates journey ETL estimated time of loading according to trajectory, 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 has entered the control correction stage and formed 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 °, body rotating speed is controlled within the scope of 5～10 turn/s ensureing.
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) stretching into for fin (5), and bearing pin (6) connects as one fin holder (4) and fin (5) through the through hole on board slot and fin (5).
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 other parts of afterbody (1).
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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| CN105865271A (en) * | 2016-05-27 | 2016-08-17 | 中国人民解放军国防科学技术大学 | Portable missile adopting fast inflatable missile wings |
| CN107101533A (en) * | 2017-06-19 | 2017-08-29 | 洛阳瑞极光电科技有限公司 | Extension type projectile correction servo control mechanism |
| CN109253667A (en) * | 2018-08-31 | 2019-01-22 | 江西洪都航空工业集团有限责任公司 | A kind of Missile Folding rudder face longitudinal direction unfolding mechanism |
| CN109472073A (en) * | 2018-10-30 | 2019-03-15 | 中国运载火箭技术研究院 | A kind of aerodynamic configuration of aircraft method of adjustment, device and electronic equipment |
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| CN105865271A (en) * | 2016-05-27 | 2016-08-17 | 中国人民解放军国防科学技术大学 | Portable missile adopting fast inflatable missile wings |
| CN107101533A (en) * | 2017-06-19 | 2017-08-29 | 洛阳瑞极光电科技有限公司 | Extension type projectile correction servo control mechanism |
| CN109253667A (en) * | 2018-08-31 | 2019-01-22 | 江西洪都航空工业集团有限责任公司 | A kind of Missile Folding rudder face longitudinal direction unfolding mechanism |
| 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 |
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| CN114036651A (en) * | 2022-01-11 | 2022-02-11 | 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 |
| 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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