CN113899255B - Accurate control rocket with control cabin section and glide range-increasing cabin section - Google Patents
Accurate control rocket with control cabin section and glide range-increasing cabin section Download PDFInfo
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- CN113899255B CN113899255B CN202111010176.1A CN202111010176A CN113899255B CN 113899255 B CN113899255 B CN 113899255B CN 202111010176 A CN202111010176 A CN 202111010176A CN 113899255 B CN113899255 B CN 113899255B
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- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 31
- 238000005096 rolling process Methods 0.000 claims abstract description 19
- 238000012937 correction Methods 0.000 claims abstract description 17
- 230000009467 reduction Effects 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 18
- 230000008569 process Effects 0.000 claims description 16
- 238000009434 installation Methods 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 7
- 238000009987 spinning Methods 0.000 claims description 6
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- 238000005259 measurement Methods 0.000 claims description 5
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- 230000000087 stabilizing effect Effects 0.000 claims description 2
- 230000003416 augmentation Effects 0.000 description 23
- 230000001965 increasing effect Effects 0.000 description 14
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- 239000003380 propellant Substances 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- 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
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
- F42B10/06—Tail fins
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- 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
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
Abstract
The invention discloses a rocket overall scheme for carrying out glide range increase and precise control by using a range increase cabin section and a control cabin section, which realizes precise control of range increase and landing points. The rocket head is added with a control cabin section, a correction rudder on the control cabin section generates aerodynamic force in the direction of a vertical control surface in flight, and the aerodynamic force direction is controlled by rolling a duck rudder seat on the control cabin section, so that accurate control of a landing point is realized; the middle part is added with a range-increasing cabin section, a pair of deployable lift wings on the range-increasing cabin section generate aerodynamic force perpendicular to the wing surface direction in flight, and the direction of the aerodynamic force is controlled through rolling the range-increasing cabin Duan Yi seat so as to realize gliding range-increasing. The rotary rudder and the rotary wing mainly provide rotary torque reduction, and realize rotary reduction of a duck rudder seat and a range-increasing cabin Duan Yi seat and control torque serving as a load balance control motor. According to the general rocket scheme, accurate control of the rocket landing point can be achieved on the basis of effectively improving the rocket flight distance.
Description
Technical Field
The invention relates to a rocket overall scheme for realizing glide range increase by using a range increasing cabin section and realizing precise control of flight by using a control cabin section, which realizes precise control of the range increase and the landing point of a rocket.
Background
The complex application scene brings high requirements on the cost-effectiveness ratio and the accurate control performance of the rocket, and the modern rocket system is promoted to develop towards the control accuracy and the target remodelling. Meanwhile, the rapid innovation of technology, in particular the rapid development of electronic information technology, provides powerful technical support for the development of rocket from uncontrolled to autonomous guidance.
The traditional rocket is generally an application carrier with inaccurate requirements on the action range, and the development of the landing point accurate control technology and the glide range-increasing technology ensures that the rocket which can only perform regional action has the possibility of performing remote accurate action on a certain region. Along with the continuous promotion and development of rocket technology, the modern application mode and space requirements are greatly changed, and the increase of the flight distance of the traditional rocket and the improvement of the action precision of a long-distance area become an important direction of the development of the modern rocket.
The flight distance of the rocket in the initial design needs to meet the application condition and the requirement is just that: such as may cover the general extent of the region of action. The larger and better the effective flight distance of the rocket is in consideration of the application requirements and the system efficiency, but the influence of factors such as the mass of the rocket body, the load mass, the production cost and the like on the manufacturing process and the launching performance is larger, so that the unlimited increase of the flight distance cannot be realized; when the mass of the whole rocket is constrained by conditions, the addition of the propellant can improve the flight distance but simultaneously reduce the load carrying mass of the load compartment. The glide range-increasing can achieve a better balance between range-increasing and carrier-maintaining capabilities, and has been developed as a research hotspot of the current range-increasing technology.
Traditional gliding increase journey rocket mainly controls the gliding increase journey through the steering engine that adopts different pneumatic overall arrangement, and rocket structure and control mechanism are more complicated, and general gliding increase journey and accurate control of landing point can't be realized through single control mode, have very big degree increased structural quality and structural complexity. On the other hand, the traditional gliding extended range rocket is not suitable for informationized transformation of the traditional inventory uncontrolled rocket due to the fact that the pneumatic layout is changed.
Disclosure of Invention
The technical solution of the invention is as follows:
in order to improve the flying distance of the rocket and the precision of the landing point, the method is provided, and the landing point of the rocket is accurately controlled by controlling the rolling angle of the duck rudder seat on a control cabin additionally arranged on the head of the rocket and controlling the aerodynamic direction generated by the correction rudder in the flying process on the control cabin; and the rolling angle of the Duan Yi seats of the range-increasing cabin on the range-increasing cabin section additionally arranged in the middle of the rocket is controlled, so that the aerodynamic direction generated by the lift wing of the range-increasing cabin section in the flight process is controlled, and the range of the rocket is increased in a gliding manner.
The technical solution of the invention is as follows:
a precision control rocket with a control cabin and a glide augmentation cabin comprising: the load control device comprises a load control assembly (1), a control cabin section (2), a load cabin (3), a range-extending cabin section (4), an engine (5) and a tail wing assembly (6); the load control assembly (1) is positioned at the head of the rocket, the control cabin section (2) is connected with the load control assembly (1) and positioned behind the control cabin section (2), the load cabin (3) is connected with the control cabin section (2) and positioned behind the control cabin section, the range-increasing cabin section (4) is connected with the load cabin section (3) and positioned behind the load cabin section (4), the tail wing assembly (6) is arranged outside a spray pipe (25) of the engine (5) and positioned at the tail of the rocket.
The control cabin section (2) of the accurate control rocket with the control cabin section and the glide range increasing cabin section comprises a control cabin section seat (7), a duck rudder seat (8), a correction rudder (9), an anti-rotation rudder (10), a bearing (11) and a control cabin section control motor (12).
The range-increasing cabin section (4) of the precise control rocket with the control cabin section and the gliding range-increasing cabin section comprises a range-increasing cabin Duan Yi seat (13), a lift wing (14), a rotor-reducing wing (15), a middle rotating shaft connecting piece (16), a bearing (17), a power module (18), a gesture measuring assembly (19), a control assembly (20), a GPS and Beidou antenna assembly (21) and a range-increasing cabin section control motor (22).
The tail assembly (6) of the precise control rocket with the control cabin section and the glide range cabin section comprises a tail seat (23) and a tail (24).
The precise control rocket with the control cabin section and the glide range cabin section comprises a control cabin section (2) which is structurally connected with a load cabin (3) and a load control assembly (1) through a control cabin section seat (7), and a duck rudder seat (8) of the control cabin section (2) is connected with the control cabin section seat (7) through a bearing (11) and can rotate relative to the control cabin section seat (7).
The load cabin (3) of the accurate control rocket with the control cabin section and the gliding range-increasing cabin section is structurally connected with the engine (5) through an intermediate rotating shaft connecting piece (16) of the range-increasing cabin section (4), the intermediate rotating shaft connecting piece (16) is a rotating shaft of the range-increasing cabin Duan Yi seat (13) rotating around an arrow body shaft, and the intermediate rotating shaft connecting piece (16) is connected with the range-increasing cabin Duan Yi seat (13) through a bearing (17).
The accurate control rocket control cabin section (2) with the control cabin section and the glide range increasing cabin section comprises a pair of correction rudders (9) arranged on a duck rudder seat (8) and provided with a reverse installation offset angle, and aerodynamic force in the direction of a vertical rudder surface in the same direction can be generated in the rocket flight process, so that aerodynamic load is provided for accurate rocket control; the pair of mounted rotary rudders (10) have a same directional mounting offset angle, can generate aerodynamic force in the direction of a reverse vertical control surface in the rocket flight process, comprehensively represent aerodynamic moment around the axis direction of the rocket body, can realize rotary reduction of the duck rudder mount (8), and can be used as control moment of a control cabin control motor (12) included in the load balance control cabin (2).
The extended range cabin section (4) of the precise control rocket with the control cabin section and the gliding extended range cabin section comprises a pair of foldable lifting wings (14) mounted on a Duan Yi seat (13) of the extended range cabin, the pair of foldable lifting wings have a reverse mounting offset angle, and aerodynamic forces in the same direction and vertical airfoil direction can be generated in the rocket flight process, so that pneumatic loads are provided for rocket extended range or precise control; the pair of foldable rotary wings (15) has a same directional installation offset angle, can generate reverse aerodynamic force in the vertical airfoil direction during rocket flight, comprehensively represents aerodynamic moment around the axis direction of the rocket body, can realize the rotary reduction of the base (13) of the range-increasing cabin Duan Yi, and can be used as the control moment of the range-increasing cabin section control motor (22) included in the load balance range-increasing cabin section (4).
The tail seat (23) of the tail assembly (6) of the accurate control rocket with the control cabin section and the glide range increasing cabin section is fixedly arranged on the outer side of a spray pipe (25) of the engine (5), and six foldable tail wings (24) which are uniformly distributed in the circumferential direction are arranged on the tail seat (23) of the tail assembly (6). The foldable tail wing (24) arranged on the tail wing seat (23) has a same-direction installation offset angle, so that aerodynamic force along the same direction along the circumferential direction can be generated in the rocket flight process, the aerodynamic moment is comprehensively expressed as an aerodynamic moment around the axis direction of the rocket body, the pneumatic loading and the spinning of the whole rocket body part can be realized, and the whole rocket body part can maintain a relatively stable rotation speed in the flight process; the foldable tail wing (24) arranged on the tail wing seat (23) has no installation offset angle, only plays a role in stabilizing during the rocket flight, and does not generate pneumatic loading effect on the rocket body.
A control cabin section control motor (12) with a control cabin section and a glide range increasing cabin section for precisely controlling a rocket control cabin section is arranged between a control cabin section seat (7) and a duck rudder seat (8), a rotor part (26) of the control cabin section control motor (12) is fixedly connected with the control cabin section seat (7), and a stator part (27) of the control cabin section control motor (12) is fixedly connected with the duck rudder seat (8). When the rocket body is in a spin state, the rotating speed of the motor (12) can be controlled by controlling the control cabin section, so that the control of the rolling direction of the duck rudder seat (8) is realized; when the rocket body is in a non-rotating state, the control of the rolling direction of the duck rudder mount (8) can be realized directly by controlling the relative rotation angles of the rotor part (26) and the stator part (27) of the control cabin section control motor (12).
The cabin-increasing section control motor (22) with the control cabin section and the gliding cabin-increasing section for precisely controlling the rocket cabin-increasing section is arranged between the middle rotating shaft connecting piece (16) and the cabin-increasing Duan Yi seat (13), a rotor part (28) of the cabin-increasing section control motor (22) is fixedly connected with the middle rotating shaft connecting piece (16), and a stator part (29) of the cabin-increasing section control motor (22) is fixedly connected with the cabin-increasing Duan Yi seat (13). When the rocket body is in a spin state, the rotation speed of the motor (22) can be controlled by controlling the range-increasing cabin section, so that the rolling direction of the range-increasing cabin Duan Yi seat (13) can be controlled; when the rocket body is in a non-rotating state, the control of the rolling direction of the extended range cabin Duan Yi seat (13) can be realized directly by controlling the relative rotation angle of the rotor part (28) and the stator part (29) of the extended range cabin section control motor (22).
The accurate control rocket with the control cabin section and the glide range-increasing cabin section carries out the following accurate control implementation process of the glide range-increasing:
after the rocket is launched, a tail wing (24) arranged on the tail wing assembly (6) is unfolded, and for the rocket body spinning scheme, the tail wing (24) plays a role in pneumatically loading to maintain the rotating speed and stability of the rocket body; for the no-rotation scheme of the rocket body, the tail wing (24) plays a role in flight stabilization; the duck rudder seat (8) on the control cabin section (2) rotates freely.
And the lift wings (14) and the rotor wings (15) on the lift cabin section (4) are unfolded near the highest point of the rocket flight path, the roll angle of the lift cabin Duan Yi seat (13) relative to the ground coordinate system is controlled in real time through the lift cabin section control motor (22), so that aerodynamic force generated by the lift wings (14) is ensured to be along the normal direction outside the flight path curve, and the glide lift of the rocket is realized.
In the vicinity of the highest point of the rocket flight trajectory, a gesture measuring assembly (19), a GPS and Beidou antenna assembly (21) are used for measuring and a control assembly (20) is used for calculating the deviation and the direction of a rocket landing point and a desired landing point to generate a control instruction, the control instruction is transmitted to a control cabin section (2) through a connecting line (30) embedded in a load cabin (3) (the informatization transformation of the rocket can be realized through a wireless transmission module), a control cabin section control motor (12) on the control cabin section (2) is used for controlling the roll angle of a duck rudder seat (8) relative to a ground coordinate system in real time according to the control instruction, so that aerodynamic force born by a correction rudder (9) is along the deviation opposite direction of the landing point, and the accurate control correction of the landing point is implemented on the rocket
The invention has the beneficial effects that:
1. according to the precise control rocket with the control cabin section and the glide range cabin section, the rolling direction of the control cabin section is controlled in real time, so that the aerodynamic direction of the correction rudder is along the deviation opposite direction of the landing point, the precise control of the landing point of the rocket can be realized, and the system efficiency of the rocket is effectively improved.
2. According to the precise control rocket with the control cabin section and the glide range cabin section, the rolling direction of the lift wing of the range cabin section is controlled in real time, so that the aerodynamic direction of the lift wing is always along the direction of the outer normal line of the flight track curve, the glide performance of the rocket can be improved to the maximum extent, and the flight distance of the rocket is effectively increased.
3. According to the precise control rocket with the control cabin section and the glide range increasing cabin section, the rolling direction of the rudder is corrected through the real-time control of the control cabin section, so that the rocket has certain maneuverability, the flexibility of the rocket is improved to a certain extent, and the action range of the rocket is enlarged.
4. According to the precise control rocket with the control cabin section and the glide range increasing cabin section, two schemes of rocket body spin and rocket body non-spin can be adopted, and only by changing the tail wing assembly part structure, the conversion of the rocket from a low-speed rolling rocket to a non-rolling rocket can be realized, so that the adaptability of the rocket to a launching platform is wider.
5. The accurate control rocket with the control cabin section and the glide range-increasing cabin section can be used for improving the existing stock rocket, and the range-increasing and drop-point accurate control of the original rocket can be realized only by additionally installing the control cabin section between the load control assembly and the load cabin and additionally installing the range-increasing cabin section between the load cabin and the engine, so that the informatization improvement of the existing traditional rocket can be realized under the condition of low cost.
Drawings
FIG. 1 is a schematic view of the overall and subsystems of the present invention in a fully deployed state of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment;
FIG. 2 is a front view of the invention in a fully deployed state of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment;
FIG. 3 is a left side view of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment in a fully deployed state of the present invention;
FIG. 4 is a top view of the precision controlled rocket with control cabin and glide augmentation cabin of the present invention in a fully deployed state;
FIG. 5 is a schematic illustration of a precisely controlled rocket folding with a control cabin and a glide augmentation cabin according to the present invention;
FIG. 6 is a schematic illustration of the precisely controlled rocket tail deployed state with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 7 is a schematic diagram of the control pod assembly and its components of a precision control rocket with a control pod and a glide slope according to the present invention;
FIG. 8 is a front view of a control pod of the present invention with a control pod and a glide augmentation pod for precision control rockets;
FIG. 9 is a left side view of a control pod of the present invention with a control pod and a glide augmentation pod for precision control rockets;
FIG. 10 is a top view of a control pod of the present invention with a control pod and a glide augmentation pod for precision control rockets;
FIG. 11 is a cross-sectional view of a control pod of the present invention with a control pod and a glide augmentation pod for precision control rockets;
FIG. 12 is a schematic view of the overall and components of a precision controlled rocket with a control pod and a glide augmentation pod of the present invention;
FIG. 13 is a front view of a precision controlled rocket with a control cabin and a glide augmentation cabin according to the present invention;
FIG. 14 is a left side view of a precision controlled rocket with a control cabin and a glide augmentation cabin of the present invention;
FIG. 15 is a top view of a precision controlled rocket with a control cabin and a glide augmentation cabin according to the present invention;
FIG. 16 is a cross-sectional view of a precision controlled rocket with a control cabin and a glide augmentation cabin according to the present invention;
FIG. 17 is a schematic view of the fin assembly and components of a precision control rocket with a control cabin and a glide augmentation cabin of the present invention;
FIG. 18 is a front view of a tail assembly of a precision control rocket with a control cabin segment and a glide slope cabin segment of the present invention;
FIG. 19 is a left side view of a tail assembly of a precision control rocket with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 20 is a top view of a tail assembly of a precision control rocket with a control cabin segment and a glide slope cabin segment according to the present invention;
FIG. 21 is a schematic view of a corrected rudder mount offset angle of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 22 is a schematic view of the rudder mount bias angle of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 23 is a schematic view of the lift wing mounting offset angle of a precision control rocket with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 24 is a schematic view of the reduced rotor mounting bias angle of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 25 is a schematic view of the tail mounting offset angle of a precision controlled rocket with a control cabin segment and a glide augmentation cabin segment of the present invention;
FIG. 26 is a schematic illustration of a precision controlled rocket glide range and precision control with a control cabin segment and a glide range extension cabin segment according to 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 4, a precision control rocket with a control cabin and a glide slope cabin according to the present invention comprises: the system comprises a load control assembly (1), a control cabin section (2), a load cabin (3), a range-extending cabin section (4), an engine (5) and a tail wing assembly (6), wherein the control cabin section (2) and the range-extending cabin section (4) are connected with each other through a connecting line (30) which is pre-buried in the load cabin (3) (the information interconnection can be realized through a wireless transmission module for the informatization transformation of a rocket); the load control assembly (1) is positioned at the head of the rocket, the control cabin section (2) is connected with the load control assembly (1) and positioned behind the control cabin section (2), the load cabin (3) is connected with the control cabin section (2) and positioned behind the control cabin section, the range-increasing cabin section (4) is connected with the load cabin section (3) and positioned behind the load cabin section (4), the tail wing assembly (6) is arranged outside a spray pipe (25) of the engine (5) and positioned at the tail of the rocket.
As shown in fig. 7-11, the control cabin (2) comprises a control cabin seat (7), a duck rudder seat (8), a correction rudder (9), an anti-rotation rudder (10), a bearing (11) and a control cabin control motor (12). The duck rudder seat (8) of the control cabin section (2) is connected with the control cabin section seat (7) through a bearing (11) and can rotate relative to the control cabin section seat (7). A pair of correction rudders (9) and a pair of rotation reduction rudders (10) are arranged on the duck rudder stand (8).
As shown in fig. 12-16, the extended range cabin section (4) comprises an extended range cabin Duan Yi seat (13), a lifting wing (14), a rotor reduction wing (15), a middle rotating shaft connecting piece (16), a bearing (17), a power module (18), an attitude measurement assembly (19), a control assembly (20), a GPS and Beidou antenna assembly (21) and an extended range cabin section control motor (22). The load cabin (3) is structurally connected with the engine (5) through an intermediate rotating shaft connecting piece (16) of the range-increasing cabin section (4), the intermediate rotating shaft connecting piece (16) is a rotating shaft of the range-increasing cabin Duan Yi seat (13) rotating around an arrow body shaft, and the intermediate rotating shaft connecting piece (16) is connected with the range-increasing cabin Duan Yi seat (13) through a bearing (17). A pair of foldable lift wings (14) and a pair of foldable rotor wings (15) are mounted on the deck Duan Yi base (13).
As shown in fig. 17-20, the tail assembly (6) comprises a tail seat (23) and a tail (24), and is fixedly arranged on the outer side of a spray pipe (25) of the engine (5). Six foldable tails (24) which are uniformly distributed in the circumferential direction are arranged on a tail seat (23) of the tail assembly (6).
21-25, the correction rudder (9), the rotary reducing rudder (10), the lifting wing (14), the rotary reducing wing (15) and the tail wing (24) in the rocket body spinning scheme all have an installation offset angle forming a certain included angle with the rocket body axis direction, and aerodynamic force vertical to the control surface and the airfoil direction can be generated in the rocket flight process.
The invention relates to a precise control rocket with a control cabin section and a glide range cabin section for performing a control specific implementation process of a glide range Cheng Jingque, which comprises the following steps:
as shown in FIG. 5, before the rocket is launched, the lift wing, the rotor wing and the tail wing are all in a folded state, and the folded rocket does not exceed the envelope size of the rocket body;
as shown in fig. 6, after the rocket is launched, the tail wing (24) on the tail wing assembly (6) is fully unfolded, and for the rocket body spinning scheme, the tail wing (24) plays a role of pneumatically loading to maintain the rotating speed and stability of the rocket body; for the no-rotation scheme of the rocket body, the tail wing (24) plays a role in flight stabilization; the duck rudder seat (8) on the control cabin section (2) rotates freely.
As shown in fig. 1, near the highest point of the rocket flight path, lift wings (14) and rotor-reducing wings (15) on the extended-range cabin section (4) are unfolded, and the roll angles of a duck rudder mount (8) and an extended-range cabin Duan Yi mount (13) relative to a ground coordinate system are controlled in real time through a control cabin section control motor (12) on the controlled cabin section and an extended-range cabin section control motor (22) on the extended-range cabin section (4), so that accurate control of the gliding extended range and landing point of the rocket is realized, and the method specifically comprises the following steps:
1) As shown in fig. 26, the attitude measurement assembly (19), the GPS and the beidou antenna assembly (21) are used for measuring and calculating the deviation and the direction of a rocket landing point and an expected landing point by the control assembly (20), a control instruction is generated, the control instruction is transmitted to the control cabin section (2) through a connecting line (30) embedded in the load cabin (3) (the informatization transformation of the rocket can be realized through a wireless transmission module), a control cabin section control motor (12) on the control cabin section (2) is used for controlling the rolling angle of the duck rudder seat (8) relative to the ground coordinate system in real time according to the control instruction, so that aerodynamic force born by the correction rudder (9) is along the deviation opposite direction of the landing point, and the accurate control correction of the landing point is implemented on the rocket;
2) As shown in fig. 26, the roll angle of the cabin increasing Duan Yi seat (13) relative to the ground coordinate system is controlled in real time by the cabin increasing control motor (22) on the cabin increasing section (4), so that aerodynamic force born by the lift wing (14) is always along the normal direction outside the flight track curve, and the gliding and range increasing effects on the rocket in the flight process are realized.
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 (8)
1. An accurate control rocket with a control cabin section and a glide range cabin section, which is characterized in that: the control cabin section realizes accurate control of a falling point of a rocket, and the range-increasing cabin section realizes glide range increase of a rocket flight distance, and consists of a load control assembly (1), a control cabin section (2), a load cabin (3), a range-increasing cabin section (4), an engine (5) and a tail wing assembly (6);
the load control assembly (1) is positioned at the head of the rocket, the control cabin section (2) is structurally connected with the load cabin (3) and the load control assembly (1) through the control cabin section seat (7), the control cabin section (2) is positioned between the load control assembly (1) and the load cabin (3), the range-increasing cabin section (4) is connected with the load cabin (3), the load cabin (3) is structurally connected with the engine (5) through a middle rotating shaft connecting piece (16) of the range-increasing cabin section (4), the engine (5) is positioned behind the range-increasing cabin section (4), the tail wing assembly (6) is arranged outside a spray pipe (25) of the engine (5) and positioned at the tail of the rocket, and transmission of control instructions generated by the range-increasing cabin section (4) to the control cabin section (2) is realized through a connecting line (30) buried in the load cabin (3) or transmission of control instructions is realized through a wireless module;
a pair of correction rudders (9) are arranged on a duck rudder seat (8) included in the control cabin section (2) and have a reverse installation offset angle, so that aerodynamic force in the direction of the same vertical rudder surface can be generated in the rocket flight process, and aerodynamic load is provided for accurate rocket control;
the pair of rotary rudders (10) mounted on the duck rudder seat (8) included in the control cabin section (2) has a same-direction mounting offset angle, can generate aerodynamic force in the reverse vertical control surface direction in the rocket flight process, comprehensively represents aerodynamic moment around the arrow body axis direction, can realize rotary reduction of the duck rudder seat (8), and can be used as control moment of the control cabin section control motor (12) included in the load balance control cabin section (2);
a pair of foldable lift wings (14) mounted on a range-increasing cabin Duan Yi seat (13) included in the range-increasing cabin section (4) have a reverse mounting offset angle, and can generate aerodynamic forces in the same direction in the vertical airfoil direction during rocket flight, so that aerodynamic loads are provided for rocket range-increasing and accurate control;
a pair of foldable rotor-reducing wings (15) mounted on a deck Duan Yi seat (13) included in the deck section (4) has a same directional mounting offset angle, and can generate reverse aerodynamic force in the vertical airfoil direction during rocket flight, the aerodynamic force can be used as aerodynamic moment around the axis direction of an rocket body, the rotor-reducing of the deck Duan Yi seat (13) can be realized, and the aerodynamic force can be used as control moment of a deck section control motor (22) included in the load-balancing deck section (4).
2. A precision control rocket with a control cabin and a glide slope cabin as defined in claim 1, wherein: the control cabin (2) comprises a control cabin seat (7), a duck rudder seat (8), a correction rudder (9), an anti-rotation rudder (10), a bearing (11) and a control cabin control motor (12);
the duck rudder seat (8) of the control cabin section (2) is connected with the control cabin section seat (7) through a bearing (11) and can rotate relative to the control cabin section seat (7);
a pair of correction rudders (9) and a pair of rotation reduction rudders (10) are fixedly arranged on the duck rudder seat (8);
the control cabin section control motor (12) on the control cabin section (2) is arranged between the control cabin section seat (7) and the duck rudder seat (8), a rotor part (26) of the control cabin section control motor (12) is fixedly connected with the control cabin section seat (7), and a stator part (27) of the control cabin section control motor (12) is fixedly connected with the duck rudder seat (8).
3. A precision control rocket with a control cabin and a glide slope cabin as defined in claim 1, wherein: the range-increasing cabin section (4) comprises a range-increasing cabin Duan Yi seat (13), a lift wing (14), a rotor-reducing wing (15), a middle rotating shaft connecting piece (16), a bearing (17), a power module (18), a gesture measuring assembly (19), a control assembly (20), a GPS and Beidou antenna assembly (21) and a range-increasing cabin section control motor (22);
the extended-range cabin Duan Yi seat (13) is connected to the middle rotating shaft connecting piece (16) through a bearing (17), and the middle rotating shaft connecting piece (16) is a rotating shaft for rotating the extended-range cabin Duan Yi seat (4) around the arrow body shaft;
a pair of foldable lifting wings (14) and a pair of foldable subtracting wings (15) are arranged on the extended-range cabin Duan Yi seat (13) and can be folded and unfolded relative to the extended-range cabin Duan Yi seat (13);
a range-increasing section control motor (22) of the range-increasing section (4) is arranged between the middle rotating shaft connecting piece (16) and the range-increasing section Duan Yi seat (13), a rotor part (28) of the range-increasing section control motor (22) is fixedly connected with the middle rotating shaft connecting piece (16), and a stator part (29) of the range-increasing section control motor (22) is fixedly connected with the range-increasing section Duan Yi seat (13);
the GPS and Beidou antenna assembly (21) is fixedly connected to the outer surface of the range-extending cabin Duan Yi seat (13) and is used for receiving GPS and Beidou satellite signals;
the attitude measurement assembly (19) is arranged between the middle rotating shaft connecting piece (16) and the extended range cabin Duan Yi seat (13) to realize the measurement of the relative rotation angle between the extended range cabin Duan Yi seat (13) and the middle rotating shaft connecting piece (16);
the power module (18) and the control assembly (20) are arranged in the middle rotating shaft connecting piece (16), the control assembly (20) is used for realizing accurate control instruction calculation of the rocket and implementing control on the control cabin section control motor (12) and the range-increasing cabin section control motor (22), and the power module (18) is used for providing power supply on the rocket.
4. A precision control rocket with a control cabin and a glide slope cabin as defined in claim 1, wherein: the tail assembly (6) comprises a tail seat (23) and a tail (24);
the tail seat (23) is fixedly arranged at the outer side of a spray pipe (25) of the engine (5);
six foldable tails (24) which are uniformly distributed in the circumferential direction are arranged on a tail seat (23) included in the tail assembly (6);
the foldable tail wing (24) arranged on the tail wing seat (23) has a same-direction installation offset angle, so that aerodynamic force along the same direction along the circumferential direction can be generated in the rocket flight process, the aerodynamic moment is comprehensively expressed as aerodynamic moment around the axis direction of the rocket body, the pneumatic loading and the spinning of the whole rocket body part can be realized, and the whole rocket body part can maintain a relatively stable rotation speed in the flight process.
5. A precision control rocket with a control cabin and a glide slope cabin as recited in claim 4, wherein: the foldable tail wing (24) arranged on the tail wing seat (23) has no installation offset angle, only plays a role in stabilizing during the rocket flight, and does not generate pneumatic loading effect on the rocket body.
6. A precision control rocket with a control cabin and a glide slope cabin as defined in claim 1, wherein: when the rocket body is in a spin state, the rotating speed of the motor (12) can be controlled by controlling the control cabin section, so that the control of the rolling direction of the duck rudder seat (8) is realized; when the rocket body is in a non-rotating state, the control of the rolling direction of the duck rudder mount (8) can be realized directly by controlling the relative rotation angles of the rotor part (26) and the stator part (27) of the control cabin section control motor (12).
7. A precision control rocket with a control cabin and a glide slope cabin as defined in claim 1, wherein: when the rocket body is in a spin state, the rotation speed of the motor (22) can be controlled by controlling the range-increasing cabin section, so that the rolling direction of the range-increasing cabin Duan Yi seat (13) can be controlled; when the rocket body is in a non-rotating state, the control of the rolling direction of the extended range cabin Duan Yi seat (13) can be realized directly by controlling the relative rotation angle of the rotor part (28) and the stator part (29) of the extended range cabin section control motor (22).
8. The precise control rocket with a control cabin section and a glide range extension cabin section according to claim 1, wherein the precise control implementation process of the glide range extension is as follows:
after the rocket is launched, the tail fin (24) arranged on the tail fin assembly (6) is unfolded, and the tail fin (24) plays a role in pneumatically loading to maintain the rotating speed and stability of the rocket body in a spinning state of the rocket body; for the non-rotating state of the rocket body, the tail wing (24) plays a role in flight stabilization; the duck rudder seat (8) on the control cabin section (2) rotates freely;
the lift wings (14) and the rotor wings (15) on the lift cabin section (4) are unfolded near the highest point of the rocket flight path, the roll angle of the lift cabin Duan Yi seat (13) relative to the ground coordinate system is controlled in real time through the lift cabin section control motor (22), aerodynamic force generated by the lift wings (14) is ensured to be along the normal direction outside the flight path curve, and the glide lift of the rocket is realized;
near the highest point of the rocket flight track, the attitude measurement assembly (19), the GPS and the Beidou antenna assembly (21) are used for measuring, the control assembly (20) is used for calculating the deviation and the direction of a rocket landing point and an expected landing point, a control instruction is generated, the control instruction is transmitted to the control cabin section (2) through a connecting line (30) buried in the load cabin (3), or the control instruction transmission is realized through a wireless transmission module, the control cabin section control motor (12) on the control cabin section (2) is used for controlling the rolling angle of the duck rudder seat (8) relative to the ground coordinate system in real time according to the control instruction, so that aerodynamic force born by the correction rudder (9) is along the deviation opposite direction of the landing point, and the accurate control correction of the landing point is implemented on the rocket.
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| CN116105554A (en) * | 2023-01-07 | 2023-05-12 | 湖北航天技术研究院总体设计所 | Terminal guidance rocket projectile |
| CN117308701B (en) * | 2023-09-07 | 2024-03-12 | 河北斐然科技有限公司 | Be applied to autogyration fin device and aircraft of aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001030653A1 (en) * | 1999-10-26 | 2001-05-03 | Gosudarstvenny Kosmichesky Nauchno-Proizvodstvennytsentr Im. M.V.Khrunicheva | Reusable booster for the first stage of a launcher |
| CN106871742A (en) * | 2017-01-05 | 2017-06-20 | 北京航天自动控制研究所 | A kind of control system being arranged on body |
| CN212458140U (en) * | 2020-05-22 | 2021-02-02 | 北京振华领创科技有限公司 | Cylinder subsonic small missile |
| CN213300979U (en) * | 2020-09-04 | 2021-05-28 | 北京恒星箭翔科技有限公司 | Guidance projectile body that 40mm rocket tube sought with general strapdown |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE0502509L (en) * | 2005-11-15 | 2007-01-09 | Bae Systems Bofors Ab | Under-calibrated grenade with long range |
| US8319164B2 (en) * | 2009-10-26 | 2012-11-27 | Nostromo, Llc | Rolling projectile with extending and retracting canards |
| US8367993B2 (en) * | 2010-07-16 | 2013-02-05 | Raytheon Company | Aerodynamic flight termination system and method |
| US9194678B2 (en) * | 2012-04-25 | 2015-11-24 | Wilcox Industries Corp. | Modular rocket system |
-
2021
- 2021-08-31 CN CN202111010176.1A patent/CN113899255B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001030653A1 (en) * | 1999-10-26 | 2001-05-03 | Gosudarstvenny Kosmichesky Nauchno-Proizvodstvennytsentr Im. M.V.Khrunicheva | Reusable booster for the first stage of a launcher |
| CN106871742A (en) * | 2017-01-05 | 2017-06-20 | 北京航天自动控制研究所 | A kind of control system being arranged on body |
| CN212458140U (en) * | 2020-05-22 | 2021-02-02 | 北京振华领创科技有限公司 | Cylinder subsonic small missile |
| CN213300979U (en) * | 2020-09-04 | 2021-05-28 | 北京恒星箭翔科技有限公司 | Guidance projectile body that 40mm rocket tube sought with general strapdown |
Non-Patent Citations (1)
| Title |
|---|
| 滑翔增程弹箭滑控段弹体运动模式对增程效率的影响;史金光;王中原;曹小兵;张冰凌;;兵工学报(第06期);第651-655页 * |
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