阅读说明：本技术 一种采用卷弧翼实现滑翔增程及精确控制的火箭 (Rocket for realizing gliding range extension and accurate control by adopting rolling arc wings ) 是由 王�华 程浩 翟小丽 苏建利 冯修源 马超越 魏炜 黄海鹏 于 2021-08-31 设计创作，主要内容包括：本发明公开了一种利用控制舱段进行滑翔增程及落点精确控制的火箭总体方案,实现增程及落点精确控制。火箭中部增加控制舱段,其上的一对可折叠展开具有反向安装偏置角的卷弧式升力翼可在飞行中产生垂直翼面方向的气动力,通过控制控制舱段翼座相对地面坐标系的滚转角度,控制气动力方向,实现对火箭增程以及对落点精确控制；其上的一对可折叠展开具有同向安装偏置角的卷弧式减旋翼提供减旋力矩,实现对控制舱段翼座的减旋及平衡控制舱段控制电机的控制力矩。采用卷弧形式的升力翼及减旋翼有效改善了火箭折叠状态及展开状态的气动整形效果,可最大限度减小飞行阻力。本发明描述的火箭总体方案,在有效提高飞行距离基础上实现对落点的精确控制。(The invention discloses a rocket overall scheme for utilizing a control cabin section to carry out precise control on gliding range increase and landing points, and the precise control on the range increase and the landing points is realized. The middle part of the rocket is additionally provided with a control cabin section, a pair of foldable and unfoldable arc-rolled lifting wings with reverse installation offset angles can generate aerodynamic force in the direction vertical to a wing surface in flight, and the aerodynamic force direction is controlled by controlling the roll angle of a wing seat of the control cabin section relative to a ground coordinate system, so that the rocket is extended to a distance and the landing point is accurately controlled; a pair of foldable and unfoldable rolling arc type rotation reducing wings with equidirectional installation offset angles provide rotation reducing torque, and rotation reduction of a control cabin wing seat and control torque of a control cabin control motor are balanced. The adoption of the arc-shaped winding type lifting wing and the rotor reducing wing effectively improves the pneumatic shaping effect of the folded state and the unfolded state of the rocket, and can reduce the flight resistance to the maximum extent. The rocket overall scheme described by the invention realizes accurate control of the landing point on the basis of effectively improving the flight distance.)

1. The utility model provides an adopt and roll up rocket of arc wing realization glide and increase journey and accurate control which characterized in that includes: the device comprises a load control assembly (1), a load cabin (2), a control cabin section (3), an engine (4) and a tail wing assembly (5); the load control assembly (1) is located at the head of the rocket, the load cabin (2) is located behind the load control assembly (1), the control cabin section (3) is connected with the load cabin (2) and located behind the load cabin, the engine (4) is connected with the control cabin section (3) and located behind the control cabin section (3), and the tail wing assembly (5) is installed on the outer side of a spray pipe (16) of the engine (4) and located at the tail of the rocket.

2. The rocket of claim 1, wherein the gliding range-extending and precise control is realized by using rolling arc wings, and the rocket comprises: the control cabin section (3) comprises a control cabin section wing seat (6), a rolling arc type lifting wing (7), a rolling arc type rotor reduction wing (8), a middle rotating shaft connecting piece (9), a bearing (10), a power supply module (11), an attitude measuring assembly (12), a control assembly (13), a GPS (global positioning system) and Beidou antenna assemblies (14), a control motor (15), a lifting wing rotating shaft (21), a lifting wing installation piece (22), a lifting wing installation piece rotating shaft (23) and a rotor reduction wing rotating shaft (24).

3. A rocket according to claim 1 and claim 2, wherein said rocket adopts a rolling arc wing to realize gliding range-increasing and precise control, characterized in that: the load cabin (2) is structurally connected with the engine (4) through a middle rotating shaft connecting piece (9) of the control cabin section (3), the middle rotating shaft connecting piece (9) is a rotating shaft of the control cabin section wing seat (6) rotating around an arrow body shaft, and the middle rotating shaft connecting piece (9) is connected with the control cabin section wing seat (6) through a bearing (10).

4. The rocket of claim 2, wherein the gliding range-extending and precise control is realized by using rolling arc wings, and the rocket comprises: and a pair of foldable rolling arc type lifting wings (7) and a pair of foldable rolling arc type rotor reducing wings (8) are arranged on a control cabin wing seat (6) of the control cabin section (3).

5. A rocket for realizing gliding, increasing range and accurate control by adopting a rolling arc wing according to claim 4, characterized in that: the arc-rolling type lifting wing (7) and the arc-rolling type rotor reducing wing (8) effectively improve the shaping effect of the aerodynamic shape of the rocket in a folded state and an unfolded state, and meanwhile, the arc-rolling type wing surface form is adopted, so that the wing area of the lifting wing can be effectively improved, and the range extending effect of the rocket is further improved under the limited space constraint.

6. A rocket for realizing gliding, increasing range and accurate control by adopting a rolling arc wing according to claim 4, characterized in that: a pair of foldable rolling arc type lifting wings (7) arranged on a wing seat (6) of the control cabin section has a reverse installation offset angle, and can generate equidirectional aerodynamic force vertical to the direction of a wing surface in the rocket flying process to provide aerodynamic load for rocket range extending or precise control.

7. A rocket for realizing gliding, increasing range and accurate control by adopting a rolling arc wing according to claim 4, characterized in that: the pair of foldable curled arc type lifting wings (7) installed on the control cabin wing seat (6) are connected to a lifting wing installation part (22) through a lifting wing rotating shaft (21), and the lifting wing installation part (22) is connected to the control cabin wing seat (6) through a lifting wing installation part rotating shaft (23).

8. A rocket as claimed in claim 7, wherein said rocket is characterized in that: the pair of curling-arc type lifting wings (7) connected to the lifting wing installation part (22) through the lifting wing rotating shaft (21) can obtain the installation angle required by the curling-arc type lifting wings (7) through the rotation of the lifting wing installation part rotating shaft (23).

9. A rocket for realizing gliding, increasing range and accurate control by adopting a rolling arc wing according to claim 4, characterized in that: a pair of foldable rolling arc type rotor reducing bodies (8) are arranged on the control cabin section wing seat (6) through a rotor reducing body rotating shaft (24) and have a same-direction installation offset angle, aerodynamic force which is opposite and vertical to a wing surface direction can be generated in the rocket flying process, the aerodynamic force is comprehensively expressed as aerodynamic moment around the arrow body axis direction, the rotation reduction of the control cabin section wing seat (6) can be realized, and meanwhile, the aerodynamic force can be used as control moment of a control motor (15) included in a load balancing control cabin section (3).

10. The rocket of claim 1, wherein the gliding range-extending and precise control is realized by using rolling arc wings, and the rocket comprises: the tail assembly (5) comprises a tail wing seat (17) and a tail wing (18).

11. A rocket for realizing gliding range-extending and precise control by using a rolling arc wing according to claim 1 and claim 10, wherein: the tail wing seat (17) is fixedly arranged on the outer side of a spray pipe (16) of the engine (4).

12. A rocket for realizing gliding range-extending and precise control by using a rolling arc wing according to claim 1 and claim 10, wherein: six foldable tail wings (18) which are uniformly distributed in the circumferential direction are arranged on a tail wing seat (17) of the tail wing assembly (5).

13. A rocket for realizing gliding range-extending and precise control by using a rolling arc wing according to claim 1 and claim 10, wherein: the foldable empennage (18) arranged on the empennage seat (17) has a same-direction installation offset angle, can generate aerodynamic force along the same direction in the circumferential direction in the rocket flying process, is comprehensively expressed as aerodynamic moment around the rocket body axis direction, can realize pneumatic loading and rotation of the whole rocket body part, and ensures that the whole rocket body part maintains a relatively stable rotation speed in the flying process.

14. A rocket for realizing gliding range-extending and precise control by using a rolling arc wing according to claim 1 and claim 10, wherein: the foldable tail wing (18) arranged on the tail wing seat (17) has no installation offset angle, only plays a stabilizing role in the rocket flying process, and does not generate pneumatic loading effect on the rocket body.

15. A rocket according to claim 1 and claim 2, wherein said rocket adopts a rolling arc wing to realize gliding range-increasing and precise control, characterized in that: the control motor (15) is arranged between the middle rotating shaft connecting piece (9) and the control cabin wing seat (6), a rotor part (19) of the control motor (15) is fixedly connected with the middle rotating shaft connecting piece (9), and a stator part (20) of the control motor (15) is fixedly connected with the control cabin wing seat (6).

16. A rocket for realizing gliding, range-extending and precise control by using rolling arc wings according to claim 1 and claim 15, wherein: when the rocket body is in a self-rotating state, the control of the rolling direction of the control cabin wing seat (6) can be realized by controlling the rotating speed of the control motor (15); when the rocket body is in a non-rotating state, the control of the rolling direction of the wing seat (6) of the control cabin section can be realized directly by controlling the relative rotation angle of the rotor part (19) and the stator part (20) of the control motor (15).

17. The rocket of claim 1, wherein the gliding and the precise control are implemented as follows:

after the rocket is launched, the tail wing (18) arranged on the tail wing component (5) is unfolded, and for the rocket body spinning scheme, the tail wing (18) plays a role in maintaining the rotating speed and the stability of the rocket body through pneumatic loading; for the arrow body non-rotation scheme, the tail wing (18) plays a role in flight stabilization.

Near the highest point of the flight path of the rocket, the arc-rolling type lifting wing (7) and the arc-rolling type reduction wing (8) on the control cabin section (3) are both unfolded, and the control cabin section wing seat (6) is controlled in real time through a control motor (15) to control the roll angle relative to a ground coordinate system, so that four different control actions on the rocket are realized:

1) the control motor (15) controls the control cabin wing seat (6) to roll an angle relative to a ground coordinate system in real time, so that aerodynamic force borne by the rolling arc type lifting wing (7) can realize the gliding and range-extending effects on the rocket along the direction of the normal outside the flight track curve;

2) the attitude measurement component (12), the GPS and the Beidou antenna component (14) are used for measuring and calculating the deviation amount and direction of a rocket drop point and an expected drop point by the control component (13), and giving a control instruction, and the control motor (15) is used for controlling the rolling angle of the control cabin wing seat (6) relative to a ground coordinate system in real time according to the control instruction, so that aerodynamic force borne by the rolling arc type lifting wing (7) has aerodynamic force components in the normal direction outside a flight track curve and the reverse direction of the drop point deviation, and the precise control on the rocket drop point is implemented while the rocket is glided and extended;

3) the attitude measurement component (12), the GPS and the Beidou antenna component (14) are used for measuring and calculating the deviation amount and direction of a rocket drop point and an expected drop point by the control component (13), a control instruction is given, and the control motor (15) controls the rolling angle of the control cabin wing seat (6) relative to a ground coordinate system in real time according to the control instruction, so that the aerodynamic force borne by the rolling arc type lifting wing (7) is opposite to the drop point deviation, and the precise control correction of the drop point is carried out to the rocket to the maximum extent;

4) at the tail section of the rocket flight, the control motor (15) controls the rotation angle of the cabin wing seat (6) relative to the ground coordinate system according to the current flight track direction, so that the aerodynamic force borne by the rolling arc type lifting wing (7) realizes the posture adjustment of the tail section of the rocket flight along the normal direction in the flight track curve, thereby increasing the falling angle of the rocket and improving the action efficiency in specific application.

Technical Field

The invention relates to a general scheme of a rocket for utilizing a control cabin section to perform gliding range extension and precise control of flight tracks, which realizes the range extension of the rocket and the precise control of a rocket landing point.

Background

The complex application scene puts higher requirements on the cost-to-efficiency ratio and the accurate control performance of the rocket, and promotes the development of a modern rocket system towards the direction of control accuracy and target remoteness. Meanwhile, the rapid innovation of the technology, especially the rapid development of the electronic information technology, provides powerful technical support for the development of the rocket from uncontrolled to autonomous guidance.

The traditional rocket is an application carrier with non-precise requirements on the action range, and the development of a landing point precise control technology and a gliding range-extending technology enables the rocket which can only perform regional action to have the possibility of performing remote precise action on a certain region. With the continuous promotion and development of rocket technology, the modern application mode and space requirement are changed greatly, 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 requirements of application conditions: such as may cover the approximate extent of the region of action. Considering the effective flying distance of the rocket to be larger and better from the aspects of application requirements and system efficiency, the influence on the manufacturing process and the launching performance is larger due to the factors such as the mass of the rocket body, the load quality and the production cost, and the like, so that the flying distance can not be increased without limit; when the full rocket mass is constrained by conditions, adding propellant can increase the flight distance but at the same time reduce the load mass that can be carried by the load compartment. The gliding range-extending can achieve better balance between range-extending and carrying capacity keeping, and has been developed as a research hotspot of the current range-extending technology.

Traditional gliding increases journey rocket mainly is through the steering engine control gliding that adopts different aerodynamic configuration increases journey, and rocket structure and control mechanism are more complicated, and generally the gliding increases journey and the accurate control of placement can't realize through single control mode, and to a great extent has increased structural mass and structural complexity. On the other hand, the traditional gliding extended-range rocket is not suitable for informatization transformation of the traditional inventory uncontrolled rocket due to the change of the pneumatic layout.

Because the size constraint of a launching platform is required during rocket design, the lift-drag ratio of the rocket in the flight process is improved to the maximum extent under the limited enveloping size constraint condition, so that a better gliding range-extending effect is achieved, and the development of the gliding range-extending rocket is restricted to a certain extent. Therefore, increasing the lift-drag ratio (mainly increasing lift and reducing drag) during the flight of the rocket under the constraint of limited space has become a main direction for the development of the gliding extended-range rocket.

Disclosure of Invention

The technical problem of the invention is solved:

in order to improve the flying distance and the accuracy of a landing point of the rocket, a control cabin section scheme which is in a mode of adding a cambered wing in the middle of the rocket and can effectively improve the lift-drag ratio in the flying process is provided, the roll angle of the control cabin section is controlled, the aerodynamic direction generated by the lift wing on the control cabin section in the flying process is further controlled, the gliding range is extended to the rocket, and the landing point of the rocket is accurately controlled.

The technical solution of the invention is as follows:

a rocket adopting a rolling arc wing to realize gliding range extension and accurate control comprises: the device comprises a load control assembly (1), a load cabin (2), a control cabin section (3), an engine (4) and a tail wing assembly (5); the load control assembly (1) is located at the head of the rocket, the load cabin (2) is located behind the load control assembly (1), the control cabin section (3) is connected with the load cabin (2) and located behind the load cabin, the engine (4) is connected with the control cabin section (3) and located behind the control cabin section (3), and the tail wing assembly (5) is installed on the outer side of a spray pipe (16) of the engine (4) and located at the tail of the rocket.

The control cabin section (3) of the rocket adopting the rolling arc wings to realize gliding range extension and accurate control comprises a control cabin section wing seat (6), rolling arc type lifting wings (7), rolling arc type reduction wings (8), a middle rotating shaft connecting piece (9), a bearing (10), a power module (11), an attitude measurement assembly (12), a control assembly (13), a GPS and Beidou antenna assembly (14), a control motor (15), a lifting wing rotating shaft (21), a lifting wing installation piece (22), a lifting wing installation piece rotating shaft (23) and a reduction wing rotating shaft (24).

The load cabin (2) and the engine (4) of the rocket adopting the cambered wings to realize gliding range extension and accurate control are structurally connected through a middle rotating shaft connecting piece (9) of the control cabin section (3), the middle rotating shaft connecting piece (9) is a rotating shaft for the wing seat (6) of the control cabin section to rotate around a rocket body shaft, and the middle rotating shaft connecting piece (9) is connected with the wing seat (6) of the control cabin section through a bearing (10).

The control cabin section (3) of the rocket for realizing gliding range extension and accurate control by adopting the curling wings comprises a control cabin section wing seat (6) on which a pair of foldable curling wing type lifting wings (7) are arranged, and the foldable curling wing type lifting wings have a reverse installation offset angle, can generate equidirectional aerodynamic force vertical to the airfoil surface direction in the rocket flying process and provide aerodynamic load for rocket range extension or accurate control; a pair of foldable rolling arc type rotor reducing wings (8) arranged on the control cabin wing seat (6) have a same-direction installation offset angle, can generate opposite aerodynamic force vertical to the wing surface direction in the rocket flying process, comprehensively shows aerodynamic moment around the arrow body axis direction, can realize the rotation reduction of the control cabin wing seat (6), and can be used as the control moment of a control motor (15) included in the load balance control cabin (3).

The pair of cambered rolling type lifting wings (7) which are connected to the lifting wing installation part (22) through the lifting wing rotating shaft (21) of the rocket for realizing gliding range extension and accurate control by adopting the cambered rolling wings can obtain the installation offset angle required by the cambered rolling type lifting wings (7) through the rotation of the lifting wing installation part rotating shaft (23); the arc-rolling type lifting wing (7) and the arc-rolling type rotor reducing wing (8) effectively improve the shaping effect of the aerodynamic shape of the rocket in a folded state and an unfolded state, and meanwhile, the arc-rolling type wing surface form is adopted, so that the wing area of the lifting wing can be effectively improved, and the range extending effect of the rocket is further improved under the limited space constraint.

The empennage assembly (5) of the rocket adopting the cambered rolling wings to realize gliding range extension and accurate control comprises an empennage seat (17) and an empennage (18), wherein the empennage seat (17) is fixedly arranged on the outer side of a spray pipe (16) of an engine (4).

Six foldable tail wings (18) which are uniformly distributed in the circumferential direction are arranged on a tail wing seat (17) of the rocket assembly (5) adopting the arc rolling wings to realize gliding range extension and accurate control, the foldable tail wings (18) arranged on the tail wing seat (17) have a same-direction installation offset angle, aerodynamic force along the circumferential direction and the same direction can be generated in the rocket flying process and comprehensively expressed as aerodynamic moment around the rocket body axis direction, the aerodynamic loading and rotation of the whole rocket body part can be realized, and the whole rocket body part maintains a relatively stable rotation speed in the flying process; the foldable tail wing (18) arranged on the tail wing seat (17) has no installation offset angle, only plays a stabilizing role in the rocket flying process, and does not generate pneumatic loading effect on the rocket body.

The control motor (15) of the rocket for realizing gliding range extension and accurate control by adopting the rolling arc wings is arranged between the middle rotating shaft connecting piece (9) and the control cabin section wing seat (6), the rotor part (19) of the control motor (15) is fixedly connected with the middle rotating shaft connecting piece (9), and the stator part (20) of the control motor (15) is fixedly connected with the control cabin section wing seat (6).

When the rocket body is in a self-rotating state, the control of the rolling direction of the wing seat (6) of the control cabin section can be realized by controlling the rotating speed of the control motor (15); when the rocket body is in a non-rotating state, the control of the rolling direction of the wing seat (6) of the control cabin section can be realized directly by controlling the relative rotation angle of the rotor part (19) and the stator part (20) of the control motor (15).

The precise control realization process of the gliding range extension of the rocket adopting the rolling arc wings to realize the gliding range extension and the precise control is as follows:

after the rocket is launched, the tail wing (18) arranged on the tail wing component (5) is unfolded, and for the rocket body spinning scheme, the tail wing (18) plays a role in maintaining the rotating speed and the stability of the rocket body through pneumatic loading; for the arrow body non-rotation scheme, the tail wing (18) plays a role in flight stabilization.

Near the highest point of the flight path of the rocket, the arc-rolling type lifting wing (7) and the arc-rolling type reduction wing (8) on the control cabin section (3) are both unfolded, and the roll angle of the wing seat (6) of the control cabin section relative to a ground coordinate system is controlled in real time through a control motor (15), so that three different control actions on the rocket are realized:

1) the control motor (15) controls the control cabin wing seat (6) to roll an angle relative to a ground coordinate system in real time, so that aerodynamic force borne by the rolling arc type lifting wing (7) can realize the gliding and range-extending effects on the rocket along the direction of the normal outside the flight track curve;

2) the attitude measurement component (12), the GPS and the Beidou antenna component (14) are used for measuring and calculating the deviation amount and direction of a rocket drop point and an expected drop point by the control component (13), and giving a control instruction, and the control motor (15) is used for controlling the rolling angle of the control cabin wing seat (6) relative to a ground coordinate system in real time according to the control instruction, so that aerodynamic force borne by the rolling arc type lifting wing (7) has aerodynamic force components in the normal direction outside a flight track curve and the reverse direction of the drop point deviation, and the precise control of the rocket drop point is implemented while the rocket is glided and extended;

3) the attitude measurement component (12), the GPS and the Beidou antenna component (14) are used for measuring and calculating the deviation amount and direction of a rocket drop point and an expected drop point by the control component (13), a control instruction is given, and the control motor (15) controls the rolling angle of the control cabin wing seat (6) relative to a ground coordinate system in real time according to the control instruction, so that the aerodynamic force borne by the rolling arc type lifting wing (7) is opposite to the drop point deviation, and the precise control correction of the drop point is carried out to the rocket to the maximum extent;

4) at the tail section of the rocket flight, the control motor (15) controls the rotation angle of the cabin wing seat (6) relative to the ground coordinate system according to the current flight direction, so that the aerodynamic force borne by the rolling arc type lifting wing (7) is along the normal direction in the flight track curve, the posture adjustment of the tail section of the rocket flight is realized, the falling angle of the rocket is increased, and the action efficiency is improved in specific application.

The invention has the beneficial effects that:

1. according to the rocket adopting the rolling arc wings to realize gliding range-increasing and accurate control, the lifting wings and the rotor reducing wings are in the rolling arc wing form, and the lift-drag ratio in the rocket flying process can be improved to the maximum extent under the constraint condition of limited enveloping size, so that better gliding range-increasing and landing point control capabilities are achieved.

2. The invention relates to a rocket for realizing gliding range extension and accurate control by adopting cambered wings, which ensures that the direction of aerodynamic force borne by a lifting wing always follows the normal direction outside a flight path curve by controlling the rolling direction of the lifting wing at a cabin section in real time, can improve the gliding performance of the rocket to the maximum extent and effectively increase the flight distance of the rocket.

3. The invention relates to a rocket for realizing gliding range extension and accurate control by adopting a curling wing, which ensures that aerodynamic force borne by a lifting wing has aerodynamic force components in the normal direction outside a flight path curve and in the opposite direction of the deviation of a landing point by controlling the rolling direction of the lifting wing at a cabin section in real time, can realize gliding range extension and accurate control of the landing point of the rocket at the same time, and effectively improves the system efficiency of the rocket.

4. The rocket adopting the cambered rolling wings to realize gliding range extension and accurate control can control the rolling direction of the lifting wing at the flight tail section by controlling the cabin section, so that the aerodynamic force borne by the lifting wing can be adjusted along the normal direction in the flight track curve, the attitude of the rocket flight tail section can be adjusted, the falling angle of the rocket falling point can be improved, and the action efficiency can be effectively improved in specific application.

5. The rocket adopting the cambered wings to realize gliding range extension and accurate control has certain maneuverability by controlling the rolling direction of the lifting wings of the cabin section in real time, improves the flexibility of the rocket to a certain extent and enlarges the action range of the rocket.

6. The rocket adopting the arc rolling wings to realize gliding range extension and accurate control can adopt two schemes of rocket body spinning and rocket body non-spinning, realizes the conversion of the rocket from a low-speed rolling rocket to a non-rolling rocket only by changing the partial structure of the empennage assembly, and can ensure that the adaptability of the rocket to a launching platform is wider.

7. The rocket adopting the cambered wings to realize gliding range extension and accurate control can be used for improving the existing rocket in storage, the range extension and the drop point of the original rocket can be accurately controlled only by additionally arranging the control cabin section between the load cabin and the engine, and the informatization improvement 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 various subsystems of the present invention in a fully deployed state of a rocket with a roll of foils for glide travel extension and precise control;

FIG. 2 is a front view of a fully deployed state of the rocket with gliding range extensions and precise control using curved wings according to the present invention;

FIG. 3 is a left side view of a fully deployed state of a rocket employing curved wings to achieve glide travel extension and precise control in accordance with the present invention;

FIG. 4 is a top view of the fully deployed state of the rocket with gliding range extensions and precise control using curved wings in accordance with the present invention;

FIG. 5 is a schematic view of a folded state of the rocket with gliding range and precise control by the rolling wings according to the present invention;

FIG. 6 is a schematic view of the rocket tail extended state of the present invention using a roll-up wing to achieve gliding extended range and precise control;

FIG. 7 is a schematic view of the control cabin section of a rocket with gliding range and precise control by using a rolling arc wing according to the present invention, and the components thereof (in an unfolded state);

FIG. 8 is a schematic view of the control cabin section of a rocket with gliding range and precise control by using a rolling arc wing according to the present invention, and the whole and the parts are shown (folded state);

FIG. 9 is a front view of a control pod section of a rocket employing curved wings for glide range extension and precision control in accordance with the present invention;

FIG. 10 is a left side view of a control bay section of a rocket employing curved wings for glide range extension and precision control in accordance with the present invention;

FIG. 11 is a top view of a control pod section of a rocket employing curved wings for glide range extension and precision control in accordance with the present invention;

FIG. 12 is a cross-sectional view of a control pod section of a rocket employing curved wings for glide extension and precision control in accordance with the present invention;

FIG. 13 is a schematic view of the deployment process of the control cabin section of a rocket with a roll-up wing for gliding and increasing range and precise control according to the present invention;

FIG. 14 is a schematic view of the tail assembly of a rocket employing cambered rolling wings for glide range extension and precise control according to the present invention;

FIG. 15 is a front view of a tail assembly of a rocket employing cambered rolling wings for glide range extension and precise control in accordance with the present invention;

FIG. 16 is a left side view of a tail assembly of a rocket employing cambered rolling wings for glide range extension and precision control in accordance with the present invention;

FIG. 17 is a top view of a tail assembly of a rocket employing cambered rolling wings for glide range extension and precision control in accordance with the present invention;

FIG. 18 is a schematic view of the installation offset angle of the lift wing of a rocket with precise control and gliding range extension by the aid of the rolling wings;

FIG. 19 is a schematic view of the reduced rotor wing installation offset angle of a rocket employing cambered rolling wings for gliding range extension and precise control according to the present invention;

FIG. 20 is a schematic view of the tail wing installation offset angle of a rocket employing cambered rolling wings to achieve gliding range extension and precise control according to the present invention;

FIG. 21 is a schematic view of a rocket gliding range-extending control mode of the present invention using a rolling-arc wing to achieve gliding range-extending and precise control;

FIG. 22 is a schematic view of the rocket gliding increment and precision control mode of the present invention using rolling wings to realize gliding increment and precision control;

FIG. 23 is a schematic view of a rocket precision control mode of the present invention using a roll-up wing to realize gliding range-extending and precision control.

FIG. 24 is a schematic view of the rocket tail attitude adjustment mode of the invention using a roll-up wing to realize glide range extension and precise control.

Detailed Description

The invention is further explained below with reference to the figures.

Example of implementation:

as shown in fig. 1-4, a rocket using a curling wing to realize gliding range-increasing and precise control according to the present invention comprises: the device comprises a load control assembly (1), a load cabin (2), a control cabin section (3), an engine (4) and a tail wing assembly (5). The load control assembly (1) is located at the head of the rocket, the load cabin (2) is located behind the load control assembly (1), the control cabin section (3) is connected with the load cabin (2) and located behind the load cabin, the engine (4) is connected with the control cabin section (3) and located behind the control cabin section (3), and the tail wing assembly (5) is installed on the outer side of a spray pipe (16) of the engine (4) and located at the tail of the rocket.

As shown in fig. 7 to 12, the control cabin (3) includes a control cabin wing seat (6), a rolling arc type lift wing (7), a rolling arc type rotor reducer (8), a middle rotating shaft connecting piece (9), a bearing (10), a power module (11), a posture measuring component (12), a control component (13), a GPS and Beidou antenna component (14), a control motor (15), a lift wing rotating shaft (21), a lift wing mounting piece (22), a lift wing mounting piece rotating shaft (23), and a rotor reducer rotating shaft (24). The load cabin (2) is structurally connected with the engine (4) through a middle rotating shaft connecting piece (9) of the control cabin section (3), the middle rotating shaft connecting piece (9) is a rotating shaft of the wing seat (6) of the control cabin section rotating around an arrow body shaft, and the middle rotating shaft connecting piece (9) is connected with the wing seat (6) of the control cabin section through a bearing (10). The control cabin wing seat (6) is connected with a lifting wing installation part (22) through a lifting wing installation part rotating shaft (23), a pair of foldable rolling arc type lifting wings (7) are installed through the lifting wing rotating shaft (21), and a pair of foldable rolling arc type reducing wings (8) are connected through a reducing rotor rotating shaft (24).

As shown in fig. 13, the deployment process of the cabin segment (3) is controlled as follows: the arc rolling type rotor reducing wing (8) rotates around a rotor reducing wing rotating shaft (24) to be unfolded; the arc-rolling type lifting wing (7) rotates and unfolds around the lifting wing rotating shaft (21) at first, and the rear lifting wing installation part (22) drives the unfolded arc-rolling type lifting wing (7) to rotate around the lifting wing installation part rotating shaft (23) so as to obtain the installation offset angle designed by the arc-rolling type lifting wing (7).

As shown in fig. 14 to 17, the tail assembly (5) comprises a tail base (17), a tail (18) fixedly mounted on the outside of the nozzle (16) of the engine (4). Six foldable tail wings (18) which are uniformly distributed in the circumferential direction are arranged on a tail wing seat (17) of the tail wing assembly (5).

As shown in fig. 18-20, the roll-arc type lift wing (7), the roll-arc type deceleration wing (8) and the tail wing (18) in the rocket body spinning scheme all have an installation offset angle forming a certain included angle with the arrow body axis direction, and aerodynamic force vertical to the wing surface direction can be generated in the rocket flying process.

The invention relates to a precise gliding range-extending control method for a rocket, which adopts an arc-rolling wing to realize gliding range-extending and precise control, and concretely comprises the following steps:

as shown in fig. 5, before the rocket is launched, the arc-rolling type lifting wing (7), the arc-rolling type decelerating wing (8) and the tail wing (18) are all in a folded state, and the folded rocket does not exceed the outer envelope size of the rocket body;

as shown in fig. 6, after the rocket is launched, the tail wings (18) arranged on the tail wing assembly (5) are completely unfolded, and for the rocket body spinning scheme, the tail wings (18) play a role in maintaining the rotating speed and stabilizing the rocket body through pneumatic loading; for the arrow body non-rotation scheme, the tail wing (18) plays a role in flight stabilization;

as shown in fig. 1, near the highest point of the rocket flight path, the control cabin section (3) is provided with a rolling arc type lifting wing (7) and a rolling arc type rotor reducing wing (8) which are both unfolded, and the control cabin section wing seat (6) is controlled in real time through a control motor (15) to control the rolling angle relative to a ground coordinate system, so that four different control actions on the rocket are realized:

1) as shown in fig. 21, the deflection angle of the cabin wing seat (6) relative to the ground coordinate system is controlled in real time through the control motor (15), so that the aerodynamic force borne by the rolling arc type lifting wing (7) always follows the direction of the outer normal of the flight track curve, and the gliding and range-extending effects on the rocket are realized;

2) as shown in fig. 22, the attitude measurement component (12), the GPS and beidou antenna component (14) are used for measuring and calculating the deviation amount and direction of the rocket landing point and the expected landing point by the control component (13), and giving a control instruction, and the control motor (15) is used for controlling the rolling angle of the control cabin wing seat (6) relative to the ground coordinate system in real time according to the control instruction, so that aerodynamic force borne by the rolling arc type lift wing (7) has aerodynamic force components in the normal direction outside the flight trajectory curve and in the opposite direction of the landing point deviation, and the rocket landing point is accurately controlled while the rocket is glided and extended;

3) as shown in fig. 23, the attitude measurement module (12), the GPS and beidou antenna module (14) are used for measuring and calculating the deviation amount and direction between the rocket drop point and the expected drop point by the control module (13), and giving a control instruction, and the control motor (15) is used for controlling the control cabin wing seat (6) to roll the angle relative to the ground coordinate system in real time according to the control instruction, so that the aerodynamic force received by the rolling arc type lifting wing (7) is opposite to the drop point deviation, and the precise control correction of the drop point is carried out to the rocket to the maximum extent;

4) as shown in fig. 24, at the last stage of the rocket flight, the control motor (15) controls the rotation angle of the cabin wing seat (6) relative to the ground coordinate system according to the current flight direction, so that the aerodynamic force exerted on the roll-arc type lift wing (7) can realize the attitude adjustment of the last stage of the rocket flight along the normal direction in the flight trajectory curve, thereby increasing the landing angle of the rocket and improving the action efficiency in specific applications.

The above description is only a preferred example of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art without departing from the spirit and principle of the present invention, and any modifications, equivalents, improvements, etc. should be included in the protection scope of the present invention.