CN117308700A - Last repair bullet medicine for realizing ballistic control by adopting control cabin section - Google Patents
Last repair bullet medicine for realizing ballistic control by adopting control cabin section Download PDFInfo
- Publication number
- CN117308700A CN117308700A CN202311111675.9A CN202311111675A CN117308700A CN 117308700 A CN117308700 A CN 117308700A CN 202311111675 A CN202311111675 A CN 202311111675A CN 117308700 A CN117308700 A CN 117308700A
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- missile
- bullet
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- 230000008439 repair process Effects 0.000 title claims abstract description 72
- 239000003814 drug Substances 0.000 title claims abstract description 34
- 238000012937 correction Methods 0.000 claims abstract description 31
- 238000009434 installation Methods 0.000 claims abstract description 16
- 238000005096 rolling process Methods 0.000 claims abstract description 15
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 8
- 230000006641 stabilisation Effects 0.000 claims description 18
- 238000011105 stabilization Methods 0.000 claims description 18
- 238000000034 method Methods 0.000 claims description 15
- 230000008569 process Effects 0.000 claims description 14
- 238000005259 measurement Methods 0.000 claims description 8
- 239000000843 powder Substances 0.000 claims description 7
- 230000009467 reduction Effects 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 claims description 3
- 238000009987 spinning Methods 0.000 claims description 2
- 238000004804 winding Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 10
- 229940079593 drug Drugs 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 239000012636 effector Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002147 killing effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an overall scheme of a last repair bullet medicine for realizing ballistic control by utilizing a control cabin section, which realizes accurate control of a drop point of the last repair bullet medicine. The tail of the last repair bullet is additionally provided with a control cabin section, a pair of foldable and unfolded correction missile wings with reverse installation offset angles can generate aerodynamic force vertical to the wing surface direction in flight, and the aerodynamic force direction is controlled by controlling the rolling angle of a wing seat of the control cabin section relative to a ground coordinate system, so that the accurate control of the drop point of the last repair bullet is realized; a pair of foldable and unfolded guide missile wings with the same-direction installation offset angle provide guide moment to realize guide and rotation of a control cabin section wing seat and balance control moment of a control cabin section control motor; in addition to the above effects, the correction missile wing with the reverse installation offset angle and the guide missile wing with the same installation offset angle together play a role in stabilizing the flying of the last repair ammunition. The general scheme of the last repair ammunition can realize accurate control of the falling point of the last repair ammunition.
Description
Technical Field
The invention relates to a general scheme of a final repair bullet medicine for realizing ballistic control by adopting a control cabin section, which realizes accurate control of a drop point of the final repair bullet.
Background
With the continuous progress of science and technology, the requirements of modern war on weapon performance are gradually increased, and indexes such as cost, precision, efficiency and the like are the most main motive force for promoting the technical progress of weapon systems. The composite warhead is widely used for attacking targets such as ground armor clusters, airport facilities and the like due to the characteristics of large damage area, strong killing property, high interception difficulty and the like of the composite warhead facing complex battlefield environments and violent attack and defense.
The throwing type ammunition carried by the primary and secondary warhead comprises two types of control and non-control, wherein the hit rate of the non-control throwing type ammunition can be influenced by multiple aspects of throwing precision, pneumatic interference and the like, and the throwing type ammunition is generally used for large-area coverage and blockage, and the striking precision is lower. The conventional guided aircraft has higher manufacturing cost, complex structure and larger occupied space, and the bullet medicine using the flight path control module has higher efficiency-cost ratio and is suitable for large-scale throwing type bullet medicine.
The impact of random factors is reduced by adding the guidance device or the flight track control module to the ammunition of the throwing sub-ammunition with the controlled flight, the scattering of drop points is reduced, the hit rate of targets is improved, and the relative accurate striking can be implemented on the targets on the sea or on the land.
Traditional end repair bullet medicine is mainly through adopting the steering wheel control of different pneumatic overall arrangement, and end repair bullet medicine structure and control mechanism are more complicated, and general ballistic control can't be realized through single control mode, have greatly increased system cost and structure complexity.
A control cabin is additionally arranged at the tail of the bullet medicine by adopting an integrated design method of a flight track control mechanism and a guidance correction module, and in the process that the bullet medicine approaches a target, the relative position of the bullet mesh is identified and a flight track control instruction is given through a GPS/Beidou positioning system and an INS system. The aerodynamic force generated by the airfoil surface with the fixed installation offset angle is utilized to carry out trajectory correction, the functions of guidance and trajectory control are achieved, and the two-dimensional accurate control of the last repair bullet medicine drop point can be realized through the one-dimensional rolling control of the airfoil surface with the fixed installation offset angle; in addition to the above effects, the correction missile wing with the reverse installation offset angle and the guide missile wing with the same installation offset angle on the control cabin section together play a role in stabilizing the flying of the last repair ammunition. .
Disclosure of Invention
The technical solution of the invention is as follows:
in order to improve the precision of the last repair bullet medicine drop point, an integrated design scheme is provided, wherein a control cabin section is additionally arranged at the tail part of the last repair bullet medicine, the rolling angle of the control cabin section relative to an inertial coordinate system is controlled, the aerodynamic force direction generated by an airfoil surface on the control cabin section in the flight process is further controlled, and the last repair bullet medicine drop point is accurately controlled.
The technical solution of the invention is as follows:
an end repair ammunition for ballistic control using a control pod includes: a fairing (1), a load cabin (2) and a control cabin section (3); the load cabin (2) is positioned behind the fairing (1), the control cabin section (3) is connected with the load cabin (2) and positioned behind the fairing, and the control cabin section (3) is positioned at the tail end of the bullet.
The control cabin section (3) for realizing ballistic control of the end repair ammunition by adopting the control cabin section comprises a control cabin section wing seat (4), a correction missile wing (5), a stabilization missile wing (6), a middle rotating shaft connecting piece (7), a rear end connecting piece (8), a GPS and Beidou antenna assembly (9), a circuit board rear cabin cover (10), a bearing (11) and a thermal battery module (12), wherein the circuit module comprises a motor driving plate (13), a control board (14), an attitude measurement INS module (15), a control motor (16), a stabilization missile wing rotating shaft (17), a correction missile wing rotating shaft (18) and a magnetic encoder assembly (19).
The load cabin (2) of the last repair ammunition realizing ballistic control by adopting the control cabin section is structurally connected with the rear end connecting piece (8) and the GPS and Beidou antenna assembly (9) through the middle rotating shaft connecting piece (7) of the control cabin section (3), the middle rotating shaft connecting piece (7) is a rotating shaft for the wing seat (4) of the control cabin section rotating around the last repair ammunition body shaft, and the wing seat (4) of the control cabin section is connected with the middle rotating shaft connecting piece (7) through a bearing (18).
The control cabin section (3) for realizing ballistic control by adopting the control cabin section comprises a control cabin section wing seat (4), a pair of foldable correction wings (5) are arranged on the control cabin section wing seat, the foldable correction wings have a reverse installation offset angle, and aerodynamic force in the same direction and vertical airfoil direction can be generated in the flight process of the final repair bullet, so that pneumatic load is provided for accurate control of the landing point of the final repair bullet; a pair of foldable stable missile wings (6) arranged on the control cabin section wing seat (4) have a same directional installation offset angle, can generate reverse aerodynamic force in the vertical airfoil direction in the flight process of the last repair missile medicine, comprehensively represent aerodynamic moment around the direction of the missile body axis, can realize the rotation reduction of the control cabin section wing seat (4), and can be used as a load moment to balance the control moment of a control motor (16) included in the control cabin section (3). In addition to the above effects, the correction missile wing with the reverse installation offset angle and the guide missile wing with the same installation offset angle together play a role in stabilizing the flying of the last repair ammunition.
A pair of foldable stabilizing missile wings (6) are installed on a control cabin section wing seat (4) of the last repair ammunition for realizing ballistic control by adopting a control cabin section, and the folding stabilizing missile wings and the correcting missile wings with reverse installation offset angles play a role in stabilizing in the flight process of the last repair missile.
The control cabin section (3) of the last repair ammunition for realizing ballistic control by adopting the control cabin section comprises a correction missile wing (5) and a stabilization missile wing (6) which are arranged on a control cabin section wing seat (4) and can be flat plate type or arc winding type missile wings.
A control motor (16) for realizing ballistic control by adopting a control cabin is arranged between a middle rotating shaft connecting piece (7) and a control cabin wing seat (4), a rotor part (21) of the control motor (16) is fixedly connected with the middle rotating shaft connecting piece (7), and a stator part (20) of the control motor (16) is fixedly connected with the control cabin wing seat (4).
The control cabin section is adopted to realize ballistic control of the last repair ammunition, and when the last repair ammunition body is in a spin state, the control of the rolling direction of the wing seat (4) of the control cabin section can be realized by controlling the rotating speed of the control motor (16); when the bullet body of the last repair bullet is in a non-rotating state, the control of the rolling direction of the wing seat (4) of the control cabin segment can be realized directly by controlling the relative rotation angles of the rotor part (21) and the stator part (20) of the control motor (16).
The implementation process of accurately controlling the drop point of the last repair bullet medicine for realizing ballistic control by adopting the control cabin section is as follows:
after the powder repair bullet medicine is thrown, the correction missile wing (5) and the stabilization missile wing (6) on the control cabin section (3) are unfolded, and for the bullet spinning scheme, the stabilization missile wing (6) plays the roles of pneumatic rotation reduction and whole missile flight stabilization on the control cabin section wing seat (4); for the non-rotation scheme of the projectile body, the stable projectile wing (6) plays a role in flight stabilization.
After the powder repair bullet medicine flight is basically stable, the rolling angle of the wing seat (4) of the cabin section relative to the ground coordinate system is controlled in real time through the control motor (16), so that the accurate control function on the powder repair bullet medicine drop point is realized:
the attitude measurement INS module (15), the GPS and the Beidou antenna assembly (9) are subjected to real-time measurement, the deviation and the direction of the final repair sub-drug predicted falling point and the expected falling point are calculated by the control board (14), a control instruction is obtained through calculation, the control motor (16) is used for controlling the rolling angle of the control cabin section wing seat (4) relative to the ground coordinate system in real time according to the control instruction, so that aerodynamic force born by the straight lifting wing (5) is along the falling point deviation opposite direction, and the accurate control of the falling point is implemented on the final repair sub-drug.
The invention has the beneficial effects that:
1. according to the end repair ammunition for realizing ballistic control by adopting the control cabin, the rolling direction of the missile wing is corrected by controlling the control cabin in real time, so that the aerodynamic force born by the corrected missile wing is along the deviation opposite direction of the falling point, the falling point of the end repair ammunition can be controlled by the ballistic force of the end repair ammunition, and the system efficiency of the end repair ammunition is effectively improved.
2. According to the end repair ammunition for realizing ballistic control by adopting the control cabin, the rolling direction of the missile wing is corrected by controlling the control cabin in real time, so that the end repair ammunition has certain maneuverability, the flexibility of the end repair ammunition is improved to a certain extent, and the action range of the end repair ammunition is enlarged.
Drawings
FIG. 1 is a schematic diagram of the overall and subsystems of the present invention in a fully deployed condition of a last repair bullet with ballistic control using a control pod;
FIG. 2 is an elevation view of a fully deployed condition of a finishing bullet with ballistic control using a control pod;
FIG. 3 is a left side view of a fully deployed condition of a last round of ballistic control using a control pod according to the present invention;
FIG. 4 is a top view of a final repair bullet with ballistic control achieved with a control pod according to the present invention in a fully deployed state;
FIG. 5 is a schematic illustration of a final repair bullet fold condition employing a control pod to achieve ballistic control in accordance with the present invention;
FIG. 6 is a schematic view of the control pod and its components (deployed state) as a whole for implementing ballistic control of a terminal ammunition using the control pod according to the present invention;
FIG. 7 is a schematic view of the control pod and its components (folded state) as a whole for implementing ballistic control of a terminal ammunition using the control pod according to the present invention;
FIG. 8 is a front view of a control pod of the present invention employing the control pod to effect ballistic control of the last round of ammunition;
FIG. 9 is a left side view of a control pod of the present invention employing the control pod to effect ballistic control of the last round of ammunition;
FIG. 10 is a top view of a control pod of the present invention employing the control pod to effect ballistic control of the last round of ammunition;
FIG. 11 is a cross-sectional view of a control pod of the present invention employing the control pod to effect ballistic control of the last round of ammunition;
FIG. 12 is a cross-sectional view of a control motor portion of an end effector cartridge employing a control pod to effect ballistic control in accordance with the present invention;
FIG. 13 is a schematic diagram of a control pod deployment process for a terminal repair ammunition employing a control pod to effect ballistic control in accordance with the present invention;
FIG. 14 is a schematic view of a corrected missile wing mounting offset angle for a terminal repair ammunition employing a control pod to effect ballistic control in accordance with the present invention;
FIG. 15 is a schematic view of a stabilizing wing mounting offset angle of a terminal repair ammunition employing a control pod to achieve ballistic control in accordance with the present invention.
Fig. 16 is a schematic illustration of the drop point precision control action of a terminal repair ammunition employing a control pod to achieve ballistic control in accordance with the present invention.
Detailed Description
The invention is further described below with reference to the drawings.
Example of implementation:
as shown in fig. 1 to 5, an end repair ammunition for ballistic control using a control pod according to the present invention includes: a fairing (1), a load cabin (2) and a control cabin section (3); the load cabin (2) is positioned behind the fairing (1), the control cabin section (3) is connected with the load cabin (2) and positioned behind the fairing, and the control cabin section (3) is positioned at the tail end of the bullet.
As shown in fig. 6-11, a control cabin (3) of the last repair ammunition for realizing ballistic control by adopting the control cabin comprises a control cabin wing seat (4), a correction missile wing (5), a stabilization missile wing (6), a middle rotating shaft connecting piece (7), a rear end connecting piece (8), a GPS and Beidou antenna assembly (9), a circuit board rear cabin cover (10), a bearing (11) and a thermal battery module (12), wherein the circuit module comprises a motor driving plate (13), a control board (14), an attitude measurement INS module (15), a control motor (16), a stabilization missile wing rotating shaft (17), a correction missile wing rotating shaft (18) and a magnetic encoder assembly (19). The load cabin (2) is structurally connected with the rear end connecting piece (8) and the GPS and Beidou antenna assembly (9) through the middle rotating shaft connecting piece (7) of the control cabin section (3), the middle rotating shaft connecting piece (7) is a rotating shaft for rotating the control cabin section wing seat (4) around the powder repair bullet body shaft, and the control cabin section wing seat (4) is connected with the middle rotating shaft connecting piece (7) through a bearing (18). A pair of foldable flat plate type correction missile wings (5) are arranged on the control cabin section missile wing seat (4) through correction missile wing rotating shafts (18), and are connected with a pair of foldable flat plate type stable missile wings (6) through stable missile wing rotating shafts (17).
As shown in fig. 12, a control motor (16) for realizing ballistic control of the end repair ammunition by using a control cabin is arranged between a middle rotating shaft connecting piece (7) and a control cabin wing seat (4), a rotor part (21) of the control motor (16) is fixedly connected with the middle rotating shaft connecting piece (7), and a stator part (20) of the control motor (16) is fixedly connected with the control cabin wing seat (4).
As shown in fig. 13, the deployment process of the control cabin segment (3) is as follows: the stable missile wing (6) rotates around a stable missile wing rotating shaft (17) to be unfolded; the correction missile wing (5) is unfolded in a rotating way around a correction missile wing rotating shaft (18).
As shown in figures 14-15, the correction missile wing (5) and the stabilization missile wing (6) are provided with a mounting offset angle forming a certain included angle with the direction of the missile body axis, and aerodynamic force perpendicular to the direction of the airfoil can be generated in the rocket flight process.
The invention relates to a specific implementation process for accurately controlling drop points of last repair bullet medicines for realizing ballistic control in a control cabin section, which comprises the following steps:
as shown in fig. 5, before the bullet medicine is thrown, the correction missile wing (5) and the stabilization missile wing (6) are in a folded state, and the size of the outer envelope of the bullet medicine is not exceeded after the bullet medicine is folded;
as shown in fig. 1 and 16, after the bullet medicine is thrown, the correction missile wing (5) and the stabilization missile wing (6) on the control cabin section (3) are both unfolded, and the rolling angle of the control cabin section wing seat (4) relative to the ground coordinate system is controlled in real time through the control motor (16), so that the accurate control of the falling point of the last repair ammunition is realized.
As shown in fig. 16, the attitude measurement INS module (15), the GPS and the beidou antenna assembly (9) are measured in real time, the deviation and the direction of the predicted landing point and the expected landing point of the last-repair bullet are calculated by the control board (14), a control instruction is obtained by calculation, the control motor (16) controls the rolling angle of the control cabin section wing seat (4) relative to the ground coordinate system in real time according to the control instruction, so that aerodynamic force received by the correction missile wing (5) is along the opposite direction of the landing point deviation, and the accurate control correction of the landing point is implemented on the last-repair bullet.
The foregoing description is only a preferred embodiment of the present invention and is not intended to limit the invention thereto, since various modifications and variations of the present invention may be made by those skilled in the art without departing from the spirit and principles of the present invention.
Claims (10)
1. An end repair ammunition for ballistic control using a control pod includes: a fairing (1), a load cabin (2) and a control cabin section (3); the load cabin (2) is positioned behind the fairing (1), the control cabin section (3) is connected with the load cabin (2) and positioned behind the fairing, and the control cabin section (3) is positioned at the tail end of the bullet.
2. The terminal ammunition for ballistic control using a control pod according to claim 1 wherein: the control cabin section (3) comprises a control cabin section wing seat (4), a correction missile wing (5), a stabilization missile wing (6), a middle rotating shaft connecting piece (7), a rear end connecting piece (8), a GPS and Beidou antenna assembly (9), a circuit board rear cabin cover (10), a bearing (11) and a thermal battery module (12), wherein the circuit module comprises a motor driving plate (13), a control board (14), a gesture measurement INS module (15), a control motor (16), a stabilization missile wing rotating shaft (17), a correction missile wing rotating shaft (18) and a magnetic encoder assembly (19).
3. A terminal ammunition for ballistic control using a control pod according to claim 1 and claim 2, wherein: the load cabin (2) is structurally connected with a rear end connecting piece (8) and a GPS and Beidou antenna assembly (9) through a middle rotating shaft connecting piece (7) of the control cabin section (3), the middle rotating shaft connecting piece (7) is a rotating shaft for rotating a control cabin section wing seat (4) around a last repair bullet body shaft, and the control cabin section wing seat (4) is connected with the middle rotating shaft connecting piece (7) through a bearing (18).
4. A terminal ammunition for ballistic control using a control pod according to claim 2 wherein: a pair of foldable correction missile wings (5) and a pair of foldable stable missile wings (6) are arranged on a control cabin section wing seat (4) included in the control cabin section (3), wherein the correction missile wings (5) and the stable missile wings (6) can be flat plate type or arc winding type missile wings.
5. The terminal ammunition for ballistic control using a control pod according to claim 4 wherein: a pair of foldable correction missile wings (5) are arranged on a control cabin section wing seat (4) through correction missile wing rotating shafts (18) and have a reverse installation offset angle, so that aerodynamic forces in the same direction and vertical airfoil directions can be generated in the flight process of the last repair bullet, and pneumatic loads are provided for accurately controlling the landing points of the last repair bullet.
6. The terminal ammunition for ballistic control using a control pod according to claim 4 wherein: a pair of foldable stable missile wings (6) are arranged on the control cabin section wing seat (4) through stable missile wing rotating shafts (17) and have a same directional installation offset angle, reverse aerodynamic force in the vertical airfoil direction can be generated in the last repair bullet medicine flight process, the aerodynamic moment is comprehensively expressed as the aerodynamic moment around the direction of the missile body axis, the rotation reduction of the control cabin section wing seat (4) can be realized, and meanwhile, the control moment of a control motor (16) included in the control cabin section (3) can be balanced as a load moment.
7. The terminal ammunition for ballistic control using a control pod according to claim 4 wherein: a pair of foldable stable missile wings (6) are installed on the control cabin section wing seat (4) through stable missile wing rotating shafts (17) without installation offset angles, and only play a role in stabilizing the last repair bullet medicine flight process.
8. A terminal ammunition for ballistic control using a control pod according to claim 1 and claim 2, wherein: the control motor (16) is arranged between the middle rotating shaft connecting piece (7) and the control cabin section wing seat (4), a rotor part (21) of the control motor (16) is fixedly connected with the middle rotating shaft connecting piece (7), and a stator part (20) of the control motor (16) is fixedly connected with the control cabin section wing seat (4).
9. A terminal ammunition for ballistic control using a control pod according to claim 1 and claim 7 wherein: when the bullet body of the last repair bullet is in a spin state, the rotation speed of the control motor (16) can be controlled to control the rolling direction of the wing seat (4) of the cabin section; when the bullet body of the last repair bullet is in a non-rotating state, the control of the rolling direction of the wing seat (4) of the control cabin segment can be realized directly by controlling the relative rotation angles of the rotor part (21) and the stator part (20) of the control motor (16).
10. The terminal ammunition for realizing ballistic control by adopting a control cabin according to claim 1, wherein the implementation process of precisely controlling the drop point is as follows:
after the powder repair bullet medicine is thrown, the correction missile wing (5) and the stabilization missile wing (6) on the control cabin section (3) are unfolded, and for the bullet spinning scheme, the stabilization missile wing (6) plays the roles of pneumatic rotation reduction and whole missile flight stabilization on the control cabin section wing seat (4); for the non-rotation scheme of the projectile body, the stable projectile wing (6) plays a role in flight stabilization.
After the powder repair bullet medicine flight is basically stable, the rolling angle of the wing seat (4) of the cabin section relative to the ground coordinate system is controlled in real time through the control motor (16), so that the accurate control function on the powder repair bullet medicine drop point is realized:
the attitude measurement INS module (15), the GPS and the Beidou antenna assembly (9) are subjected to real-time measurement, the deviation and the direction of the predicted falling point of the last repair bullet medicine and the expected falling point are calculated by the control board (14), a control instruction is obtained through calculation, the control motor (16) is used for controlling the rolling angle of the control cabin section wing seat (4) relative to the ground coordinate system in real time according to the control instruction, so that aerodynamic force born by the correction missile wing (5) is along the deviation opposite direction of the falling point, and the falling point of the last repair bullet medicine is accurately controlled.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311111675.9A CN117308700A (en) | 2023-08-31 | 2023-08-31 | Last repair bullet medicine for realizing ballistic control by adopting control cabin section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311111675.9A CN117308700A (en) | 2023-08-31 | 2023-08-31 | Last repair bullet medicine for realizing ballistic control by adopting control cabin section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117308700A true CN117308700A (en) | 2023-12-29 |
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ID=89236232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311111675.9A Pending CN117308700A (en) | 2023-08-31 | 2023-08-31 | Last repair bullet medicine for realizing ballistic control by adopting control cabin section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117308700A (en) |
-
2023
- 2023-08-31 CN CN202311111675.9A patent/CN117308700A/en active Pending
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