CN113899254B - Gliding and increasing Cheng Jingque controlled rocket with gliding and increasing range section, full rocket guide rotating wing and control assembly - Google Patents
Gliding and increasing Cheng Jingque controlled rocket with gliding and increasing range section, full rocket guide rotating wing and control assembly Download PDFInfo
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- CN113899254B CN113899254B CN202111009901.3A CN202111009901A CN113899254B CN 113899254 B CN113899254 B CN 113899254B CN 202111009901 A CN202111009901 A CN 202111009901A CN 113899254 B CN113899254 B CN 113899254B
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- 238000012937 correction Methods 0.000 claims abstract description 15
- 238000005096 rolling process Methods 0.000 claims abstract description 12
- 238000010248 power generation Methods 0.000 claims abstract description 4
- 230000003416 augmentation Effects 0.000 claims description 46
- 238000000034 method Methods 0.000 claims description 20
- 230000008569 process Effects 0.000 claims description 19
- 239000007921 spray Substances 0.000 claims description 13
- 238000009434 installation Methods 0.000 claims description 9
- 230000009467 reduction Effects 0.000 claims description 7
- 230000026683 transduction Effects 0.000 claims description 7
- 238000010361 transduction Methods 0.000 claims description 7
- 238000005259 measurement Methods 0.000 claims description 6
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims 4
- 230000001105 regulatory effect Effects 0.000 claims 1
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract 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
- F42B10/32—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, full rocket guiding and flight control by using a range increasing cabin section, a guiding cabin section and a control assembly, and realizing accurate range increase and drop point control. The middle part is added with a range-increasing cabin section, a pair of deployable lifting wings generate aerodynamic force perpendicular to the wing surface direction in flight, and the direction of the aerodynamic force is controlled by rolling a range-increasing cabin Duan Yi seat to realize gliding range increase; the guiding and rotating cabin section is added behind the range-extending cabin section, four guiding and rotating wings which can be unfolded on the guiding and rotating cabin section generate guiding and rotating moment around an arrow body shaft in flight, so that the rotating speed of the arrow body is maintained, the power generation requirement of a generator of the range-extending cabin section is met, and the flight stability is improved; a pair of correction rudders on the tail control assembly generate aerodynamic force vertical to the direction of the control surface in flight, and the aerodynamic force direction is controlled through the rolling control assembly wing seat, so that accurate control of the landing point is realized. According to the rocket overall scheme, accurate control of landing points can be achieved on the basis of effectively improving flight distance.
Description
Technical Field
The invention relates to a rocket overall scheme for carrying out glide range increase by using a range increasing cabin section, full rocket guiding and transferring by using a guiding cabin section and precise control of flight by using a control assembly, which realizes the range increase of a rocket and precise control of a rocket landing point.
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 rolling angle of a Duan Yi seat of a range-increasing cabin on a range-increasing cabin section additionally arranged in the middle of the rocket is controlled, so that the aerodynamic force generated by a lifting wing on the range-increasing cabin section in the flying process is controlled to perform gliding range-increasing on the rocket; the rotating speed of the rocket body in the rocket flight process is maintained through the guide cabin section added in the middle of the rocket, so that the relatively constant rotating speed of the extended range cabin section relative to the rocket body is ensured, and the requirement on the power generation efficiency of the extended range cabin section generator is met; the rolling angle of the control component wing seat on the control component positioned at the tail of the rocket is controlled, so that the aerodynamic force direction generated by the correction rudder in the flight process on the control component is controlled to accurately control the landing point of the rocket.
The technical solution of the invention is as follows:
a gliding increase Cheng Jingque control rocket with a gliding increase flight deck and a full rocket guide wing and control assembly, characterized by comprising: the load control device comprises a load control assembly (1), a load cabin (2), a range-extending cabin section (3), a steering cabin section (4), an engine (5) and a control assembly (6); the load control assembly (1) is positioned at the head of the rocket, the load cabin (2) is connected with the load control assembly (1) and positioned behind the load cabin, the range-increasing cabin section (3) is connected with the load cabin (2) and positioned behind the load cabin, the transduction cabin section (4) is connected with the range-increasing cabin section (3) and the engine (5), and the control assembly (6) is arranged at the outer side of a spray pipe (25) of the engine (5) and positioned at the tail of the rocket.
The gliding increase Cheng Jingque controlled rocket increase cabin section (3) with the gliding increase cabin section and the whole rocket guide rotating wings and control assembly comprises an increase cabin Duan Yi seat (7), a lifting wing (8), a reduction rotor wing (9), a middle rotating shaft connecting piece (10), a bearing (11), a power supply module (12), a gesture measuring assembly (13), an increase cabin section control assembly (14), a GPS and Beidou antenna assembly (15) and an increase cabin section control motor (16).
The gliding and increasing Cheng Jingque control rocket guiding cabin section (4) with the gliding and increasing cabin section, the whole rocket guiding wing and the control assembly comprises a guiding cabin section wing seat (17) and a guiding wing (18).
The control component (6) for controlling the rocket through the glide increment Cheng Jingque with the glide increment cabin section, the whole rocket guide wing and the control component comprises a control component wing seat (19), a correction rudder (20), an anti-rotation rudder (21), a bearing (22), a control component control module (23) and a control component control motor (24).
The utility model provides a take gliding increase cabin section and full arrow to lead wing and control assembly's gliding increase Cheng Jingque control rocket's load cabin (2) and lead and change cabin section (4) and carry out structural connection through the intermediate shaft connecting piece (10) of increase cabin section (3), intermediate shaft connecting piece (10) are the rotatory rotation axis of increase cabin Duan Yi seat (7) around the arrow body axle, intermediate shaft connecting piece (10) are connected with increase cabin Duan Yi seat (7) through bearing (11).
The glide and augmentation Cheng Jingque control rocket guide cabin section (4) with the glide and augmentation cabin section and the whole rocket guide and augmentation wing and control assembly is connected with the load cabin (2) through the middle rotating shaft connecting piece (10) and fixedly connected with the engine (5).
A control component wing seat (19) of a control component (6) with a glide increment cabin section, a full rocket guide rotating wing and a control component for controlling a rocket by a glide increment Cheng Jingque is connected with an engine spray pipe (25) through a bearing (22) and can rotate relative to the engine spray pipe (25).
The glide increment Cheng Jingque with the glide increment cabin section and the whole rocket guide rotating wing and control assembly controls a pair of foldable lifting wings (8) mounted on an increment cabin Duan Yi seat (7) included in the rocket increment cabin section (3) to have a reverse mounting offset angle, and can generate aerodynamic force in the same direction in the vertical airfoil direction in the rocket flight process so as to provide aerodynamic load for rocket increment or accurate control; the pair of foldable rotary wings (9) 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 extended range cabin Duan Yi seat (7), and can be used as the control moment of the extended range cabin section control motor (16) included in the load balance extended range cabin section (3).
The gliding increase Cheng Jingque control rocket comprises a diversion cabin section wing seat (17) provided with four foldable diversion wings (18) which are circumferentially and uniformly distributed, the four foldable diversion wings are provided with a same directional installation offset angle, aerodynamic force along the circumferential direction in the same direction can be generated in the rocket flight process, the aerodynamic force is comprehensively expressed as aerodynamic moment around the axis direction of the rocket body, and the pneumatic loading and the rotation starting of the whole rocket body part can be realized, so that the whole rocket body part maintains a relatively stable rotation speed in the flight process.
The control assembly (6) with the glide increment cabin section, the full rocket guide rotating wing and the control assembly controls the rocket, wherein the control assembly wing seat (19) is provided with a pair of foldable correction rudders (20) which have a reverse installation offset angle, and can generate aerodynamic force in the direction of the same direction vertical control surface in the rocket flight process so as to provide aerodynamic load for accurate rocket control; the two pairs (four sheets) of foldable rotary rudders (21) are provided with a same-direction installation offset angle, aerodynamic force in the direction of a reverse vertical control surface can be generated in the rocket flight process, the aerodynamic moment is comprehensively expressed as aerodynamic moment in the direction around the axis of the rocket body, the rotary reduction of a wing seat (19) of a control assembly can be realized, and meanwhile, the aerodynamic moment can be used as the control moment of a control assembly control motor (24) included in a load balance control assembly (6).
The flight augmentation cabin section control motor (16) with the flight augmentation cabin section, the whole rocket guide rotating wing and the control assembly is arranged between the middle rotating shaft connecting piece (10) and the augmentation cabin Duan Yi seat (7), a rotor part (26) of the flight augmentation cabin section control motor (16) is fixedly connected with the middle rotating shaft connecting piece (10), and a stator part (27) of the flight augmentation cabin section control motor (16) is fixedly connected with the flight augmentation cabin Duan Yi seat (7); the extended-range cabin control motor (16) has the functions of a generator and a control motor, and as the extended-range cabin Duan Yi seat (7) always has a relative rotating speed relative to the middle rotating shaft connecting piece (10), the extended-range cabin control motor (16) always has a relative rotation between the rotor part (26) and the stator part (27), so that the power generation function of the extended-range cabin control motor (16) can be realized. The rocket body is in a spin state in the rocket flight process, and the rotation speed of the motor (16) can be controlled by controlling the cabin increasing section, so that the rolling direction of the cabin increasing Duan Yi seat (7) can be controlled.
A control assembly control motor (24) with a glide cabin section, a full rocket guiding rotating wing and a control assembly for controlling a rocket in a glide Cheng Jingque mode is arranged between a control assembly wing seat (19) and an engine spray pipe (25), a rotor part (28) of the control assembly control motor (24) is fixedly connected with the engine spray pipe (25), and a stator part (29) of the control assembly control motor (24) is fixedly connected with the control assembly wing seat (19). The rocket body is in a spin state in the rocket flying process, and the control of the rolling direction of the wing seat (19) of the control assembly can be realized by controlling the rotating speed of the motor (24) through the control assembly.
The accurate control implementation process of the glide range increase Cheng Jingque control rocket with the glide range increase cabin section, the whole rocket guide rotating wing and the control assembly is as follows:
after the rocket is launched, a guide wing (18) arranged on the guide cabin section (4) is unfolded, and the guide wing (18) plays a role in pneumatically loading, maintaining the rotating speed and stabilizing of the rocket body; a correction rudder (20) and an reduction rudder (21) mounted on the control unit (6) are deployed and freely rotated.
And the lift wings (8) and the rotor wings (9) on the range-increasing cabin section (3) are unfolded near the highest point of the rocket flight track, the rolling angle of the range-increasing cabin Duan Yi seat (7) relative to the ground coordinate system is adjusted and controlled in real time through the range-increasing cabin section control motor (16), so that aerodynamic force generated by the lift wings (8) is ensured to be along the normal direction outside the flight track curve, and the gliding range increase of the rocket is realized.
Near the highest point of the rocket flight track, the attitude measurement assembly (13), the GPS and the Beidou antenna assembly (15) are used for measuring, the range-increasing cabin control assembly (14) is used for calculating the deviation and the direction of a rocket landing point and an expected landing point and giving a control command, the deviation and the direction are wirelessly transmitted to the control assembly control module (23), and the control assembly control motor (24) is used for controlling the roll angle of the control assembly wing seat (19) relative to the ground coordinate system in real time according to the control command, so that aerodynamic force born by the correction rudder (20) is in the direction opposite to the landing point deviation, and accurate control of the rocket landing point is implemented.
The invention has the beneficial effects that:
1. according to the invention, the gliding increase Cheng Jingque with the gliding increase cabin section, the whole rocket guiding rotating wing and the control assembly controls the rocket, and the rolling direction of the lift wing of the increase cabin section is controlled in real time, so that the aerodynamic force direction born by the lift wing is always along the direction of the normal outside the flight track curve, the gliding performance of the rocket can be improved to the maximum extent, and the flight distance of the rocket is effectively increased.
2. According to the invention, the gliding increment Cheng Jingque with the gliding increment cabin section, the full rocket guide rotating wings and the control assembly is used for controlling the rocket, the real-time control assembly is used for correcting the rolling direction of the rudder, so that the aerodynamic force direction of the corrected rudder is along the deviation opposite direction of the landing point, the accurate control of the landing point of the rocket can be realized, and the system efficiency of the rocket is effectively improved.
3. According to the invention, the gliding increment Cheng Jingque with the gliding increment cabin section, the full rocket guide rotating wings and the control assembly is used for controlling the rocket, and the real-time control assembly is used for correcting the rolling direction of the rudder, so that the rocket has a certain maneuvering capability, the flexibility of the rocket is improved to a certain extent, and the action range of the rocket is enlarged.
4. According to the invention, the gliding increment Cheng Jingque controlled rocket with the gliding increment cabin section, the full rocket guide rotating wing and the control assembly has the functions of generating electricity and controlling, so that the rocket load power supply requirement can be effectively reduced, and the rocket control capability is improved; meanwhile, the rotation speed of the rocket body is maintained by the guide cabin section, so that the control assembly and the rocket body always keep a relatively stable relative rotation speed, and the requirement of generating electricity by the motor of the range-extending cabin section is met.
5. The gliding increase Cheng Jingque control rocket with the gliding increase cabin section, the full rocket guide rotating wings and the control assembly can be used for improving the existing stock rocket, and the original rocket tail wing part can be improved and replaced by the control assembly only by additionally installing the increase cabin section and the guide rotating cabin section between the load cabin and the engine, so that the precise control of the increase range and the landing point of the original rocket can be realized, and the precise upgrading and transformation of the existing traditional rocket can be realized under the condition of low cost.
Drawings
FIG. 1 is a schematic diagram of the overall and subsystems of a glide increment Cheng Jingque controlled rocket in its fully deployed state with a glide increment flight deck and full rocket idler and control assembly of the present invention;
FIG. 2 is a front view of the invention in a fully deployed state of a glide augmentation Cheng Jingque control rocket with a glide augmentation flight deck and full rocket guide wing and control assembly;
FIG. 3 is a left side view of a glide increment Cheng Jingque controlled rocket with a glide increment flight deck and full rocket guide wing and control assembly of the present invention in a fully deployed state;
FIG. 4 is a top view of a fully deployed state of a glide increment Cheng Jingque controlled rocket with a glide increment flight deck and full rocket idler and control assembly of the present invention;
FIG. 5 is a schematic illustration of a glide increment Cheng Jingque controlled rocket folding with a glide increment flight deck and full rocket idler and control assembly of the present invention;
FIG. 6 is a schematic diagram of the invention in a configuration of a glide increment Cheng Jingque with a glide increment flight deck and a full rocket guide wing and control assembly for controlling the deployment of the rocket tail and guide wing;
FIG. 7 is a schematic diagram of the bulk and components of a glide augmentation Cheng Jingque controlled rocket with a glide augmentation flight deck and a full rocket guide wing and control assembly of the present invention;
FIG. 8 is a front view of a glide augmentation flight deck and full rocket guide wing and control assembly controlled rocket of the present invention with a glide augmentation flight deck Cheng Jingque;
FIG. 9 is a left side view of a glide augmentation Cheng Jingque control rocket of the present invention with a glide augmentation flight deck and a full rocket guide wing and control assembly;
FIG. 10 is a top view of a glide augmentation flight deck and full rocket guide wing and control assembly controlled rocket of the present invention with a glide augmentation flight deck Cheng Jingque;
FIG. 11 is a cross-sectional view of a glide augmentation flight deck and full rocket pilot and control assembly of the present invention with the flight augmentation Cheng Jingque control rocket;
FIG. 12 is a schematic view of the entire and various components of a glide and augmentation Cheng Jingque controlled rocket according to the present invention with a glide and augmentation flight deck and a full rocket guide wing and control assembly;
FIG. 13 is a front view of a pilot segment of a glide and augmentation Cheng Jingque control rocket with a glide and augmentation flight segment and a full rocket pilot and control assembly of the present invention;
FIG. 14 is a left side view of a glide and augmentation Cheng Jingque control rocket pod with a glide and augmentation flight deck and a full rocket guide wing and control assembly of the present invention;
FIG. 15 is a top view of a pilot segment of a glide and augmentation Cheng Jingque control rocket with a glide and augmentation flight segment and a full rocket pilot and control assembly of the present invention;
FIG. 16 is a schematic view of the control assembly and components of a glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly of the present invention;
FIG. 17 is a front view of a control assembly of the present invention with a glide augmentation flight deck and full rocket guide wing and control assembly for controlling a rocket of the present invention, glide augmentation Cheng Jingque;
FIG. 18 is a left side view of a control assembly of the glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket idler and control assembly of the present invention;
FIG. 19 is a top view of a control assembly of the glide and augmentation Cheng Jingque control rocket with a glide and augmentation flight deck and full rocket guide wing and control assembly of the present invention;
FIG. 20 is a cross-sectional view of a control assembly of the present invention with a glide augmentation flight deck and a full rocket idler and control assembly for controlling a rocket with glide augmentation Cheng Jingque;
FIG. 21 is a schematic view of the lift wing mounting offset angle of a glide augmentation Cheng Jingque control rocket with a glide augmentation flight deck and full rocket pilot and control assembly of the present invention;
FIG. 22 is a schematic view of the reduced rotor mounting offset angle of a glide augmentation Cheng Jingque control rocket with a glide augmentation flight deck and full rocket lead wing and control assembly of the present invention;
FIG. 23 is a schematic view of the pilot wing mounting offset angle of a glide augmentation Cheng Jingque control rocket with a glide augmentation flight deck and a full rocket pilot wing and control assembly of the present invention;
FIG. 24 is a schematic view of the corrected rudder mount offset angle of the glide increment Cheng Jingque controlled rocket with the glide increment flight deck and the rocket pilot rotor and control assembly of the present invention;
FIG. 25 is a schematic view of the rudder mount bias angle of a glide increment Cheng Jingque controlled rocket with a glide increment flight deck and full rocket pilot and control assembly of the present invention;
FIG. 26 is a schematic diagram of a first control of the glide slope and precision control of a rocket with a glide slope segment and a full rocket pilot wing and control assembly Cheng Jingque of the present invention;
FIG. 27 is a second schematic diagram of a glide augmentation Cheng Jingque controlled rocket glide augmentation and precision control with a glide augmentation flight deck and full rocket steering wing and control assembly of the present invention.
Detailed Description
The invention is further described below with reference to the drawings.
Example of implementation:
as shown in fig. 1-4, a glide increasing Cheng Jingque control rocket with a glide increasing flight deck and a full rocket guiding wing and control assembly of the present invention comprises: the load control device comprises a load control assembly (1), a load cabin (2), a range-extending cabin section (3), a steering cabin section (4), an engine (5) and a control assembly (6); the load control assembly (1) is positioned at the head of the rocket, the load cabin (2) is connected with the load control assembly (1) and positioned behind the load cabin, the range-increasing cabin section (3) is connected with the load cabin (2) and positioned behind the load cabin, the transduction cabin section (4) is connected with the range-increasing cabin section (3) and the engine (5), and the control assembly (6) is arranged at the outer side of a spray pipe (25) of the engine (5) and positioned at the tail of the rocket.
As shown in fig. 7-11, the extended range cabin section (3) comprises an extended range cabin Duan Yi seat (7), a lifting wing (8), a rotor reduction wing (9), a middle rotating shaft connecting piece (10), a bearing (11), a power module (12), a gesture measuring component (13), an extended range cabin section control component (14), a GPS and Beidou antenna component (15) and an extended range cabin section control motor (16). The load cabin (2) is structurally connected with the guide cabin section (4) through a middle rotating shaft connecting piece (10) of the range expansion cabin section (3), the middle rotating shaft connecting piece (10) is a rotating shaft for rotating the range expansion cabin Duan Yi seat (7) around an arrow body shaft, and the middle rotating shaft connecting piece (10) is connected with the range expansion cabin Duan Yi seat (7) through a bearing (11). A pair of foldable lift wings (8) with a reverse mounting offset angle and a pair of foldable rotor wings (9) with a same directional mounting offset angle are mounted on the booster cabin Duan Yi seat (7).
As shown in fig. 12-15, the transduction pod (4) includes a pod wing mount (17) and a transduction wing (18). The transfer cabin section (4) is connected with the load cabin (2) through an intermediate rotating shaft connecting piece (10) and is fixedly connected with the engine (5). Four guide wings (18) which are uniformly distributed in the circumferential direction and can be folded to have a same direction installation offset angle are arranged on the guide cabin section wing seat (17).
As shown in fig. 16-20, the control assembly (6) comprises a control assembly wing seat (19), a correction rudder (20), an anti-rotation rudder (21), a bearing (22), a control assembly control module (23) and a control assembly control motor (24). The control assembly wing seat (19) of the control assembly (6) is connected with the engine spray pipe (25) through a bearing (22) and can rotate relative to the engine spray pipe (25). A pair of foldable correction rudders (20) with a reverse installation offset angle and two pairs (four pieces) of foldable anti-rotation rudders (21) with a same direction installation offset angle are installed on the control assembly wing seat (19).
As shown in fig. 21-25, the lift wing (8), the rotor (9), the rotor (18), the rudder (20) and the rudder (21) all have a mounting offset angle with a certain included angle with the rocket body axis direction, and aerodynamic force vertical to the rudder surface and the airfoil direction can be generated in the rocket flight process.
The invention relates to a specific implementation process for controlling a rocket to perform glide increase Cheng Jingque by using a glide increase Cheng Jingque with a glide increase cabin section, a whole rocket guide rotating wing and a control assembly, which comprises the following steps:
as shown in FIG. 5, before the rocket is launched, the lift wing, the rotor reducing wing, the steering wing, the rotor reducing rudder and the modified rudder are all in a folded state, and the folded rocket does not exceed the envelope size outside the rocket body;
as shown in fig. 6, after the rocket is launched, the guiding wing (18) arranged on the guiding cabin section (4) is unfolded, and the guiding wing (18) plays a role in pneumatically loading, maintaining the rotating speed and stabilizing of the rocket body; the correction rudder (20) and the reduction rudder (21) which are arranged on the control assembly (6) are unfolded and freely rotate;
as shown in fig. 1, near the highest point of the rocket flight path, the lift wings (8) and the rotor wings (9) on the extended-range cabin section (3) are all unfolded, and the roll angles of the extended-range cabin Duan Yi seat (7) and the control component wing seat (19) relative to the ground coordinate system are controlled in real time by the extended-range cabin section control motor (16) on the extended-range cabin section and the control component control motor (24) on the control component, so that the accurate control of the glide extended-range and landing points of the rocket is realized, and the method specifically comprises the following steps:
1) As shown in fig. 26, the roll angle of the cabin increasing Duan Yi seat (7) relative to the ground coordinate system is controlled in real time by the cabin increasing control motor (16) on the cabin increasing section (3), so that aerodynamic force born by the lift wing (8) is always along the normal direction outside the flight track curve, and the gliding and the range increasing of the rocket are realized;
2) As shown in fig. 26, the attitude measurement assembly (13), the GPS and the beidou antenna assembly (15) are used for measuring, the range-extending cabin section control assembly (14) is used for calculating the deviation and direction of a rocket landing point and an expected landing point and giving a control command, the control command is transmitted to the control assembly control module (23) through the wireless module, the control assembly is used for controlling the roll angle of the control assembly wing seat (19) relative to the ground coordinate system in real time according to the control command by the control assembly control motor (24), so that aerodynamic force born by the correction rudder (20) is along the opposite direction of the landing point deviation, and the accurate control of the rocket landing point is implemented.
3) As shown in fig. 27, in order to improve the landing point control capability of the rocket at the end of the flight, a mode of combining the flight increasing cabin section (3) and the control component (6) can be adopted, according to the attitude measurement component (13), the GPS and the beidou antenna component (15), the deviation and the direction of the landing point of the rocket and the expected landing point calculated by the flight increasing cabin section control component (14) are measured, a control command is given, the roll angle of the seat (7) of the flight increasing cabin Duan Yi relative to the ground coordinate system is controlled in real time by the flight increasing cabin section control motor (16) according to the control command, aerodynamic force born by the lifting wing (8) has aerodynamic force components in the normal direction outside the flight track curve and in the opposite direction of the landing point deviation, and meanwhile, the accurate control capability of the landing point of the rocket is improved by combining the control mode of the control component (6) in the 2).
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. A gliding increase Cheng Jingque control rocket with a gliding increase flight deck and a full rocket guide wing and control assembly, characterized by comprising: the load control device comprises a load control assembly (1), a load cabin (2), a range-extending cabin section (3), a steering cabin section (4), an engine (5) and a control assembly (6);
the load control assembly (1) is positioned at the head of the rocket, the load cabin (2) is connected with the load control assembly (1), the range-increasing cabin section (3) is connected with the load cabin (2), the load cabin (2) is positioned between the load control assembly (1) and the range-increasing cabin section (3), the load cabin (2) and the steering cabin section (4) are structurally connected through a middle rotating shaft connecting piece (10) of the range-increasing cabin section (3), the steering cabin section (4) is fixedly connected with the engine (5), and the control assembly (6) is arranged at the outer side of a spray pipe (25) of the engine (5) and positioned at the tail of the rocket;
a pair of foldable lift wings (8) mounted on a range-increasing cabin Duan Yi seat (7) included in the range-increasing cabin section (3) 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 rotary wings (9) mounted on a base (7) of a range-increasing cabin Duan Yi included in the range-increasing cabin section (3) 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 rotary wings of the base (7) of the range-increasing cabin Duan Yi can be realized, and meanwhile, the aerodynamic force can be used as control moment of a range-increasing cabin section control motor (16) included in the load balance range-increasing cabin section (3);
two pairs of foldable guide wings (18) which are uniformly distributed in the circumferential direction and are arranged on a guide cabin section wing seat (17) included in the guide cabin section (4) are provided with a same directional installation offset angle, and aerodynamic force in the same circumferential direction can be generated in the rocket flight process and can be used as aerodynamic moment in the direction of an arrow body shaft, so that pneumatic loading and rotation 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;
a pair of correction rudders (20) arranged on a control assembly wing seat (19) of the control assembly (6) have a reverse installation offset angle, and can generate aerodynamic force in the direction of the same-direction vertical control surface in the rocket flight process so as to provide aerodynamic load for accurate rocket control;
two pairs of rotation reducing rudders (21) mounted on a control assembly wing seat (19) included in the control assembly (6) have a same directional mounting offset angle, and can generate aerodynamic force in a reverse vertical control surface direction in the rocket flight process, the aerodynamic force can be used as aerodynamic moment in the direction of an arrow body axis, the rotation reducing of the control assembly wing seat (19) can be realized, and meanwhile, the aerodynamic force can be used as control moment of a control assembly control motor (24) included in the load balancing control assembly (6).
2. A glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly as defined in claim 1 wherein: the range-increasing cabin section (3) comprises a range-increasing cabin Duan Yi seat (7), a lift wing (8), a rotor-reducing wing (9), a middle rotating shaft connecting piece (10), a bearing (11), a power module (12), a gesture measuring component (13), a range-increasing cabin section control component (14), a GPS and Beidou antenna component (15) and a range-increasing cabin section control motor (16);
the extended-range cabin Duan Yi seat (7) is connected to the intermediate rotating shaft connecting piece (10) through a bearing (11), and the intermediate rotating shaft connecting piece (10) is a rotating shaft for rotating the extended-range cabin Duan Yi seat (7) around an arrow body shaft;
a pair of foldable lifting wings (8) and a pair of foldable subtracting wings (9) are arranged on the extended-range cabin Duan Yi seat (7) and can be folded and unfolded relative to the extended-range cabin Duan Yi seat (7);
the range-increasing cabin section control motor (16) is arranged between the middle rotating shaft connecting piece (10) and the range-increasing cabin Duan Yi seat (7), a rotor part (26) of the range-increasing cabin section control motor (16) is fixedly connected with the middle rotating shaft connecting piece (10), and a stator part (27) of the control motor (16) is fixedly connected with the range-increasing cabin Duan Yi seat (7);
the GPS and Beidou antenna assembly (15) is fixedly connected to the outer surface of the range-extending cabin Duan Yi seat (7) and is used for receiving GPS and Beidou satellite signals;
the attitude measurement assembly (13) is arranged between the middle rotating shaft connecting piece (10) and the extended range cabin Duan Yi seat (7) to realize the measurement of the relative rotation angle between the extended range cabin Duan Yi seat (7) and the middle rotating shaft connecting piece (10);
the power module (12) and the range-increasing cabin section control assembly (14) are arranged inside the middle rotating shaft connecting piece (10), the range-increasing cabin section control assembly (14) is used for realizing accurate control instruction calculation of a rocket and control of a range-increasing cabin section control motor (22), and meanwhile, a control instruction is sent to a control assembly control module (23) included in the control assembly (6), and the power module (12) is used for providing an on-rocket power supply.
3. A glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly as defined in claim 1 wherein: the transduction cabin section (4) comprises a transduction cabin section wing seat (17) and a transduction wing (18);
two pairs of foldable guiding wings (18) are arranged on the guiding cabin section wing seat (17) in a circumferentially uniform distribution mode and can be folded and unfolded relative to the guiding cabin section wing seat (17).
4. A glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly as defined in claim 1 wherein: the control assembly (6) comprises a control assembly wing seat (19), a correction rudder (20), an anti-rotation rudder (21), a bearing (22), a control assembly control module (23) and a control assembly control motor (24);
the control assembly wing seat (19) is connected with the engine spray pipe (25) through a bearing (22) and can rotate relative to the engine spray pipe (25);
a pair of foldable correction rudders (20) and two pairs of foldable anti-rotation rudders (21) are arranged on the control component wing seat (19) and can be folded and unfolded relative to the control component wing seat (19);
the control assembly control motor (24) is arranged between the control assembly wing seat (19) and the engine spray pipe (25), a rotor part (28) of the control assembly control motor (24) is fixedly connected with the engine spray pipe (25), and a stator part (29) of the control motor (24) is fixedly connected with the control assembly wing seat (19);
the control module (23) is positioned between the engine nozzle (25) and the control module wing seat (19) and is used for controlling the motor (24) by receiving the control command sent by the range-increasing cabin section control module (14).
5. A glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly as defined in claim 2 wherein: the extended-range cabin control motor (16) has the functions of a generator and a control motor, and as the extended-range cabin Duan Yi seat (7) always has a relative rotating speed relative to the middle rotating shaft connecting piece (10), the extended-range cabin control motor (16) always has a relative rotation between the rotor part (26) and the stator part (27), so that the power generation requirement of the extended-range cabin control motor (16) can be met.
6. A glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly as defined in claim 1 wherein: the rocket body is in a spin state in the rocket flight process, and the rotation speed of the motor (16) can be controlled by controlling the cabin increasing section, so that the rolling direction of the cabin increasing Duan Yi seat (7) can be controlled.
7. A glide increment Cheng Jingque control rocket with a glide increment flight deck and full rocket guide wing and control assembly as defined in claim 1 wherein: the rocket body is in a spin state in the rocket flying process, and the control of the rolling direction of the wing seat (19) of the control assembly can be realized by controlling the rotating speed of the motor (24) through the control assembly.
8. The control rocket of claim 1, wherein the glide and augmentation Cheng Jingque control rocket with the glide and augmentation flight deck and the full rocket guiding wing and control assembly is characterized by the following steps:
after the rocket is launched, a guide wing (18) arranged on the guide cabin section (4) is unfolded, and the guide wing (18) plays a role in pneumatically loading, maintaining the rotating speed and stabilizing of the rocket body; the correction rudder (20) and the reduction rudder (21) which are arranged on the control assembly (6) are unfolded and freely rotate;
the lift wings (8) and the rotor wings (9) on the lift cabin section (3) are controlled to be unfolded near the highest point of the rocket flight path, the roll angle of a Duan Yi seat (7) of the lift cabin is regulated and controlled in real time relative to a ground coordinate system through a lift cabin section control motor (16), aerodynamic force generated by the lift wings (8) is ensured to be along the outer normal direction of a flight path curve, and the gliding lift of the rocket is realized;
near the highest point of the rocket flight track, the attitude measurement assembly (13), the GPS and the Beidou antenna assembly (15) are used for measuring, the range-increasing cabin control assembly (14) is used for calculating the deviation and the direction of a rocket landing point and an expected landing point and giving a control command, the deviation and the direction are wirelessly transmitted to the control assembly control module (23), and the control assembly control motor (24) is used for controlling the roll angle of the control assembly wing seat (19) relative to the ground coordinate system in real time according to the control command, so that aerodynamic force born by the correction rudder (20) is in the direction opposite to the landing point deviation, and accurate control of the rocket landing point is implemented.
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| CN202111009901.3A CN113899254B (en) | 2021-08-31 | 2021-08-31 | Gliding and increasing Cheng Jingque controlled rocket with gliding and increasing range section, full rocket guide rotating wing and control assembly |
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| CN202111009901.3A CN113899254B (en) | 2021-08-31 | 2021-08-31 | Gliding and increasing Cheng Jingque controlled rocket with gliding and increasing range section, full rocket guide rotating wing and control assembly |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9194678B2 (en) * | 2012-04-25 | 2015-11-24 | Wilcox Industries Corp. | Modular rocket system |
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2021
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| JPH06129798A (en) * | 1992-10-19 | 1994-05-13 | Mitsubishi Heavy Ind Ltd | Objective missile |
| WO2000078610A2 (en) * | 1999-05-24 | 2000-12-28 | Lockheed Martin Corporation | Fly back booster |
| CN111038699A (en) * | 2018-10-12 | 2020-04-21 | 北京理工大学 | Separable composite range extending system and method on aircraft |
| CN111121544A (en) * | 2019-12-10 | 2020-05-08 | 北京航天飞腾装备技术有限责任公司 | Accurate guidance bomb target bomb for rapid evaluation of damage efficiency |
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