Rocket-boosted rescue unmanned aerial vehicle and control method

Abstract

The invention provides a rocket-boosted rescue unmanned aerial vehicle and a control method. The rocket-boosted rescue unmanned aerial vehicle comprises a cruising stage, an interstage section and a boosting stage, the cruising stage is provided with a folding telescopic wing and a turbojet engine; in the working process of the unmanned aerial vehicle, the boosting stage quickly sends the cruising stage to the high altitude and separates the cruising stage, then the cruising stage continuously ascends to cross the highest point, and after the folding telescopic wings of the cruising stage are unfolded to slide and the speed is reduced to a low speed, the folding telescopic wings stretch out and grow and start the turbojet engine to cruise. The high acceleration capacity of the rocket engine, the wide speed range adaptive capacity of the deformable wings and the long-time cruising capacity of the turbojet engine are integrally combined, and the time for the rescue unmanned aerial vehicle to arrive at the site is effectively shortened.

Description

Technical Field

[0001] The present invention belongs to the field of unmanned aerial vehicle (UAV) rescue, and in particular, relates to a rescue UAV using rocket propulsion, and more particularly to a rescue UAV using rocket propulsion and a turbojet engine. Background Art

[0002] Drones are increasingly being used in search and rescue operations due to their flexibility, maneuverability, and rapid coverage. In recent years, with the rapid development of drone technology, their use in search and rescue has exploded. Compared to traditional rescue methods, drones offer significant advantages, including the ability to overcome terrain limitations, efficiently cover the search area, and transmit real-time on-site imagery. In scenarios such as mountain search and rescue, locating distress at sea, and surveying disaster areas, the response speed of drones is directly linked to the success rate of rescue operations. However, the existing drone technology system still faces bottlenecks that need to be overcome. Currently, mainstream rescue drones mostly use multi-rotor or fixed-wing configurations. The low cruising speed of traditional drones results in delayed average arrival times. There is a lack of technical solutions that can reach the search and rescue area more quickly and have greater environmental adaptability.

[0003] In response to the technical problems existing in the existing technology, the present invention proposes a rescue drone with rocket propulsion, which combines the high acceleration capability of the rocket engine, the wide speed range adaptability of the deformable wings, and the long-term cruising capability of the turbojet engine, effectively shortening the time it takes for the rescue drone to arrive at the scene.

[0004] Patent document CN115924075A discloses a small supersonic reusable multi-task UAV, comprising: a UAV body, a guidance system, a propulsion system, a steering gear system, a landing system, and a flight control system arranged in the UAV body; the UAV body adopts a waverider structure; the propulsion system adopts a reusable integral solid ramjet engine, which comprises: an air inlet, an isolating section, a gas generator unit, a combustion chamber, a nozzle, and a propulsion control unit; the air inlet, the isolating section, the combustion chamber, and the nozzle are arranged in sequence along the symmetry axis of the UAV body; the air inlet of the air inlet is located at the belly of the UAV body, and the nozzle of the nozzle is located at the tail of the UAV body; the gas generator unit is arranged along the symmetry axis of the UAV body and is detachably arranged in front of the combustion chamber; the combustion chamber is provided with solid rocket propellant of the integral solid ramjet engine; the combustion chamber and the nozzle are detachably arranged.

[0005] However, the solid ramjet engine used in the UAV propulsion system disclosed in patent document CN115924075A requires that its flight speed must be supersonic throughout its operation and cannot cruise at subsonic speed, which is not conducive to accurate search. In addition, the external booster (a) at the tail end of the UAV mentioned in the patent document is used to accelerate the UAV from subsonic speed to the supersonic starting speed of the solid ramjet engine.

[0006] The present invention uses rocket propulsion to deliver the drone to the target area at supersonic speed, and then cruises and searches at subsonic speed. The speed change is opposite to that of patent document CN115924075A. In addition, the folding and retractable wings (13) of the present invention have two states of high speed and low speed, which effectively increases the range, while patent document CN115924075A does not have this capability.

[0007] Patent document CN118145033A discloses a rocket-launched UAV and its operating method, including: a fuselage, front wings, rear wings, tail wings, an optoelectronic system and a power system. The optoelectronic system is installed at the front end of the fuselage. The front wings are folded and located above the fuselage. The rear wings are folded and located below the fuselage. The front wings and the rear wings are unfolded to form a serial wing layout on the fuselage. The tail wings are folded and located on both sides of the rear end of the fuselage. The power system is installed at the rear end of the fuselage. A separation ring is provided outside the power system, and the fuselage is connected to the rocket engine through the separation ring.

[0008] However, the UAV in patent document CN118145033A is powered by electric propellers, and its flight speed can only reach subsonic speed, resulting in short flight time and low search efficiency.

[0009] The present invention, however, uses turbojet propulsion, enabling high-subsonic cruise flight. Furthermore, the folding, retractable wings in the present invention have two speed settings: high and low, effectively increasing the range. Patent document CN118145033A lacks this capability and does not mention how to control the drone before it is deployed. Summary of the Invention

[0010] In view of the defects in the prior art, the purpose of the present invention is to provide a rocket-assisted rescue drone and a control method.

[0011] According to the present invention, a rocket-assisted rescue drone is provided, comprising: a cruise stage 1, an interstage section 2, and a booster stage 3; the cruise stage 1, the interstage section 2, and the booster stage 3 are connected in sequence, the cruise stage 1 is a cruise drone, and the booster stage 3 is a solid rocket engine;

[0012] The cruise stage 1 is a structure with a rectangular cross section and a conical head, and the near-conical end of the cylindrical section is the front end.

[0013] Preferably, the cruise stage 1 comprises: a main casing 11, a rudder 12, a steering gear 16, and an air inlet fairing 18;

[0014] The cruise stage 1 is a canard aerodynamic layout;

[0015] A rudder 12 is provided at the front end of the cylindrical section of the cruise stage 1; a steering gear 16 is installed near the rudder 12 to cooperate with it;

[0016] The main housing 11 is the overall outer shell of the cruise stage 1;

[0017] The maximum outer envelope diameter of the main casing 11 of the cruise stage 1 is smaller than the diameter of the booster stage 3;

[0018] The air inlet fairing 18 is connected to the main casing 11 by explosive bolts, and a spring mechanism is embedded in the connection between the two.

[0019] Preferably, the cruise stage 1 further comprises: a turbojet engine 14, a payload device 17, and a fuel tank 15;

[0020] The rudder 12 has four rudder blades, which are arranged in an X-shape or a ten-shape;

[0021] The air inlet of the turbojet engine 14 is located in the rear half of the main casing 11;

[0022] The fuel tank 15 is provided on the side of the turbojet engine 14 in the main housing 11;

[0023] The payload equipment 17 is divided into two categories: delivery payload and detection payload. The delivery payload is delivered through the hatches on both sides of the main shell 11; the detection payload is detected through the window at the bottom of the main shell 11.

[0024] Preferably, the cruise stage 1 further comprises: folding retractable wings 13;

[0025] The foldable telescopic wing 13 is located on the side of the main shell 11, and includes: an outer shell 131. The outer shell 131 is a hollow shell structure with an outer opening, and its root is connected to the main shell 11 by a rotating hinge or a rotating shaft; the outer shell 131 can rotate along the root, and the rotation angle is 90°. The specific range is that the minimum can be attached to both sides of the rectangular main shell 11, and the maximum can be perpendicular to the side of the main shell 11.

[0026] Preferably, the folding telescopic wing 13 further includes: a telescopic section 132 and a fairing 133;

[0027] The telescopic section 132 is disposed in the cavity of the shell 131 , and the telescopic section 132 can extend from the side opening of the cavity of the shell 131 , thereby increasing the wingspan;

[0028] The fairing 133 is installed at the opening on the side of the cavity of the shell 131. The edge notch of the cavity opening of the shell 131 matches the shape of the fairing 133. The fairing 133 is clamped by matching the edge notch of the cavity opening of the shell 131 through the contact surface, and is not fixed with bolts.

[0029] Preferably, a micro motor is installed in the innermost part of the cavity of the housing 131, and the telescopic section 132 is driven to move by a ball screw;

[0030] The housing 131 has a sweep angle of 60°, and the telescopic section 132 has no sweep angle;

[0031] When the telescopic section 131 is extended, the fairing 133 is pushed open and away from the shell 131 and then falls.

[0032] Preferably, the housing 131 is an airfoil suitable for high-speed flight;

[0033] The telescopic section 132 is an airfoil suitable for low-speed flight;

[0034] The wingspan is increased by repeatedly nesting the telescopic mechanism composed of the outer shell 131 and the telescopic section 132 in multiple layers;

[0035] The trailing edge of the foldable telescopic wing 13 is provided with a trailing edge rudder, which cooperates with the rudder 12 to perform attitude control.

[0036] Preferably, the booster stage 3 has no attitude and orbit control equipment; the shape is cylindrical;

[0037] The interstage section 2 is a round-to-square shell structure formed by splicing two halves of the structure, and the shells of the two halves are connected by explosive bolts;

[0038] The interstage section 2 is connected to the cruise stage 1 and the booster stage 3 located before and after the interstage section 2 by explosive bolts;

[0039] The interstage section 2 is in a sloped shape, i.e., the front opening is small and the rear opening is large;

[0040] The ratio of the length of the overall aircraft equipped with the rocket-assisted rescue drone to the diameter of the booster stage 3 is 12.

[0041] According to the present invention, a control method for a rocket-assisted rescue drone is provided, comprising:

[0042] Step S1: Active ascending stage;

[0043] Step S2: passive ascending stage;

[0044] Step S3: high-speed sliding section;

[0045] Step S4: low-speed cruising section.

[0046] Preferably, the step S1 includes: igniting the booster stage 3, accelerating the drone to take off, shutting down the booster stage 3, and separating the interstage 2;

[0047] The step S2 includes: the cruise aircraft 1 continues to rise until it passes the highest point;

[0048] The step S3 includes: folding and unfolding the retractable wings 13, and gliding at high speed in the cruise stage 1;

[0049] The step S4 includes: after the speed drops to a low speed, the telescopic wings 13 are folded and the telescopic sections 132 are extended, the air inlet fairing 18 is jettisoned, and the turbojet engine 14 is started;

[0050] During the execution of steps S1 and S2, the foldable retractable wings 13 are attached to both sides of the rectangular main housing 11;

[0051] During the execution of step S3, the foldable and retractable wings 13 rotate and unfold to be perpendicular to the side of the main housing 11;

[0052] During the execution of step S4 , based on step S3 , the telescopic section 132 is extended and the fairing 133 falls.

[0053] Compared with the prior art, the present invention has the following beneficial effects:

[0054] 1. The present invention uses rocket propulsion to propel the drone to a high altitude at high speed and glide at high speed for a certain distance, thereby increasing the average flight speed of the drone. This includes first using rocket propulsion for delivery and then using a turbojet engine for powered cruising.

[0055] 2. The low-speed turbojet engine of the present invention takes into account the need to provide continuous cruising capability;

[0056] 3. The present invention adopts a canard-style aerodynamic layout with a rudder in the front, which enables effective control throughout the entire flight process. In particular, the wings of the present invention can be folded and retracted to adapt to flight conditions over a wide speed range. The folding and retractable wings can be adjusted according to speed, with high and low speed settings. This gives the UAV a high lift-to-drag ratio and maneuverability at both low and high speeds, effectively extending its range.

[0057] 4. The present invention as a whole provides a technical solution that takes into account both rapid arrival and cruise search and rescue capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0059] Figure 1 This is a schematic diagram comparing various angles of the rocket-assisted rescue drone of the present invention.

[0060] Figure 2 It is a comparison diagram between the three-view structures of the cruise stage of the present invention.

[0061] Figure 3 It is an overall schematic diagram of the cruise stage of the present invention.

[0062] Figure 4 It is a schematic side sectional view of the cruise stage of the present invention.

[0063] Figure 5 This is a schematic diagram of the foldable telescopic wings of the present invention.

[0064] Figure 6 It is a schematic diagram of the working process of the present invention.

[0065] The figure shows:

[0066] DETAILED DESCRIPTION

[0067] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0068] like Figures 1 to 5 As shown, an embodiment of the present invention provides a rescue drone using rocket propulsion, including: a cruise stage 1, an interstage section 2 and a booster stage 3; the cruise stage 1, the interstage section 2 and the booster stage 3 are connected in sequence, the cruise stage 1 is a cruise drone, the booster stage 3 is a solid rocket engine, and the interstage section 2 is used for connection and controllable separation.

[0069] The cruise stage 1 further comprises a main hull 11, a rudder 12, folding and retractable wings 13, a turbojet engine 14, a fuel tank 15, a steering gear 16, and payload equipment 17. The main hull 11 serves as the overall outer shell of the cruise stage 1. Furthermore, the cruise stage 1 features a canard-style aerodynamic layout. The UAV utilizes a rudder 12 located at the front end of the cruise stage 1's cylindrical section, near the conical head section, for attitude control throughout its operation. The rudder 12 consists of four blades arranged in an X-shape. The cruise stage 1 has a rectangular cross-section combined with a conical head. The air intake fairing 18 is connected to the main hull 11 via explosive bolts. A spring mechanism is embedded in the connection to push the fairing away. Furthermore, to minimize interference with the airflow from the rudder 12, the turbojet engine 14's air intake is located in the rear half of the main hull 11, allowing for either ventral or dorsal air intake. Furthermore, the payload equipment 17 is divided into two categories: delivery payloads and detection payloads. Delivery payloads can be delivered through doors on both sides of the main hull 11, while detection payloads can be detected through windows in the lower portion of the main hull 11. Furthermore, a steering gear 16 is mounted near the rudder 12, and the fuel tank 15 is located near the turbojet engine 14 within the main hull 11.

[0070] Furthermore, if Figure 5 As shown, the foldable and retractable wings 13 are located on the side of the main shell 11. The foldable and retractable wings 13 include a shell 131, a telescopic section 132, and a fairing 133. The shell 131 is a hollow shell structure with an outer opening, and its base is connected to the main shell 11 by a rotating hinge or shaft. The shell 131 can rotate along its base, with a specific range of rotation of 90°, ranging from a minimum of being attached to both sides of the rectangular main shell 11 to a maximum of being perpendicular to the side of the main shell 11. The telescopic section 132 is located within the cavity of the shell 131 and can extend from the side opening of the shell 131 cavity, thereby increasing the wingspan. The fairing 133 is installed in the opening on the side of the shell 131 cavity. The notch on the edge of the shell 131 cavity opening matches the shape of the fairing 133. The fairing 133 is fixed to the notch on the edge of the shell 131 cavity opening by a contact surface, without the use of bolts or other fixed connections. When the telescopic section 131 is extended, the fairing 133 can be pushed open and away from the shell 131, thereby falling. Furthermore, a micro motor is installed in the innermost part of the cavity of the shell 131, and the telescopic section 132 is pushed to move by a ball screw. In a more specific embodiment, the sweep angle of the shell 131 is 60°, and the telescopic section 132 has no sweep angle. Furthermore, the shell 131 is a trapezoidal wing with a large leading edge sweep angle, which is suitable for high-speed flight. The setting of the telescopic section 132 can be used for low-speed flight, and an airfoil setting such as a rectangular wing can be adopted. The wingspan after low-speed extension can be further increased by repeatedly nesting the telescopic mechanism composed of multiple layers of the shell 131 and the telescopic section 132. A trailing edge rudder can be provided at the trailing edge of the folding telescopic wing 13 to cooperate with the rudder 12 for attitude control.

[0071] Furthermore, based on low cost considerations, the booster stage 3 does not have attitude and trajectory control equipment such as a tail rudder and a swing nozzle; the booster stage 3 is cylindrical; the interstage section 2 is a round-to-square shell structure formed by splicing two halves of the structure, and the shells of the two halves are connected by explosive bolts; the interstage section 2 is connected to the cruise stage 1 and the booster stage 3 located in front and behind it respectively by explosive bolts; further, the ratio of the entire aircraft length to the booster stage 3 diameter is 12; in a more specific embodiment, the booster stage 3 has a diameter of 200 mm, and the maximum diameter of the cross-section envelope of the main shell 11 is 190 mm; belly air intake is adopted, specifically, the air inlet of the turbojet engine 14 is on the lower belly of the UAV.

[0072] The embodiment of the present invention also provides a control method for a rescue drone using rocket propulsion, wherein the working process of the drone under control is as follows: Figure 6 As shown, the UAV workflow is divided into: Step S1: active ascent phase; Step S2: passive ascent phase; Step S3: high-speed glide phase; and Step S4: low-speed cruise phase. Step S1 includes: ignition of booster stage 3, the UAV launches at a high angle (the launch angle is proportional to and depends on the distance to the target area, with a maximum of 90° and generally greater than 60°), acceleration to liftoff, and separation of interstage 2 after booster stage 3 shuts down. Step S2 includes: continuous ascent of cruise stage 1 until it passes the highest point; Step S3 includes: deployment of foldable retractable wings 13, and high-speed glide of cruise stage 1. Step S4 includes: after the speed drops to a low speed, extension of retractable wings 13 and ejection of inlet fairing 18, and startup of turbojet engine 14. Furthermore, the UAV maintains a 0° angle of attack in Steps S1 and S3, reducing control difficulty. Furthermore, in steps S1 and S2, the folded telescopic wings 13 are attached to both sides of the rectangular main shell 11; in step S3, the folded telescopic wings 13 are rotated and unfolded to be perpendicular to the side of the main shell 11; in step S4, based on the execution of step S3, the telescopic section 132 is extended and the fairing 133 falls off.

[0073] More specifically, the aerodynamic layout of the rocket-assisted rescue drone described in the present invention is as follows: the cruise stage 1 has a rectangular cross-section with a conical head, while the booster stage 3 is cylindrical. The interstage section 2 is formed by joining two halves, forming a circular-to-square shell structure, connected by explosive bolts. The interstage section 2 is connected to the cruise stage 1 and booster stage 3 located in front and behind it by explosive bolts. The cruise stage 1 adopts a canard aerodynamic layout, and the drone uses a rudder 12 located at the front of the cruise stage 1 for attitude control throughout its operation. The rudder 12 consists of four blades, which can be arranged in an X- or X-shaped pattern. For low-cost considerations, the booster stage 3 lacks attitude control equipment such as tail rudder tubes. Separation of the booster stage 3 does not involve a reverse thrust engine or other separation mechanism, relying solely on aerodynamic separation. The maximum outer envelope diameter of the main casing 11 of the cruise stage 1 is smaller than the diameter of the booster stage 3, and the interstage section 2 is sloped, with a smaller front opening and a larger rear opening, to ensure that the booster stage 3 does not collide with the cruise stage 1 when separating, and further ensure that the booster stage 3 and the interstage section 2 retreat relative to the cruise stage 1 when separating.

[0074] In summary, the present invention provides a rocket-assisted rescue drone and its working process, comprising: a cruise stage 1, an interstage 2, and a booster stage 2; the booster stage 2 quickly sends the cruise stage 1 into high altitude and separates, and then the cruise stage 1 continues to rise until it passes the highest point, and the folding and retractable wings 13 of the cruise stage 1 unfold and glide, and after the speed drops to a low speed, the folding and retractable wings 13 extend and grow and start the turbojet engine 14 of the cruise stage 1 to enter cruise; the present invention combines the high acceleration capability of the rocket engine, the wide speed range adaptability of the deformable wings, and the long-term cruising capability of the turbojet engine, effectively shortening the time it takes for the rescue drone to arrive at the scene.

[0075] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0076] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A rocket-assisted rescue drone, characterized in that: include: A cruise stage (1), an interstage section (2) and a booster stage (3); the cruise stage (1), the interstage section (2) and the booster stage (3) are connected in sequence, the cruise stage (1) is a cruise UAV, and the booster stage (3) is a solid rocket engine; The cruise stage (1) is a structure with a rectangular cross section combined with a conical head, and the near-conical end of the cylindrical section is the front end.

2. The rocket-assisted rescue drone according to claim 1, characterized in that: The cruise stage (1) comprises: a main casing (11), a rudder (12), a steering gear (16), and an air inlet fairing (18); The cruise stage (1) is a canard aerodynamic layout; A rudder (12) is provided at the front end of the cylindrical section of the cruise stage (1); a steering gear (16) is installed near the rudder (12) and is arranged in coordination with the rudder (12); The main housing (11) is the overall outer shell of the cruise stage (1); The maximum outer envelope diameter of the main casing (11) of the cruise stage (1) is smaller than the diameter of the booster stage (3); The air inlet fairing (18) is connected to the main housing (11) via explosive bolts, and a spring mechanism is embedded in the connection between the two.

3. The rocket-assisted rescue drone according to claim 2, characterized in that: The cruise stage (1) further comprises: a turbojet engine (14), a payload device (17), and a fuel tank (15); The rudder (12) has four rudder blades, and the four rudder blades are arranged in an X shape or a cross shape; The air inlet of the turbojet engine (14) is located in the rear half of the main casing (11); The fuel tank (15) is arranged on the turbojet engine (14) side in the main casing (11); The load equipment (17) is divided into two categories: delivery load and detection load. The delivery load is delivered through the hatches on both sides of the main shell (11); the detection load is detected through the window at the bottom of the main shell (11).

4. The rocket-assisted rescue drone according to claim 2, characterized in that: The cruise stage (1) further comprises: folding retractable wings (13); The folding and telescopic wings (13) are located on the side of the main shell (11) and include: a shell (131); the shell (131) is a shell structure with a hollow interior and an outer opening, and its root is connected to the main shell (11) by a rotating hinge or a rotating shaft; the shell (131) can rotate along the root, with a rotation angle of 90 degrees, and the specific range is that the minimum can be attached to both sides of the rectangular main shell (11) and the maximum can be perpendicular to the side of the main shell (11).

5. The rocket-assisted rescue drone according to claim 4, characterized in that: The folding telescopic wing (13) further includes: a telescopic section (132) and a fairing (133); The telescopic section (132) is arranged in the cavity of the shell (131), and the telescopic section (132) can extend from the side opening of the cavity of the shell (131), thereby increasing the wingspan; The fairing (133) is mounted on an opening on the side of the cavity of the housing (131); the notch on the edge of the cavity opening of the housing (131) matches the outer shape of the fairing (133); the fairing (133) is clamped by matching the notch on the edge of the cavity opening of the housing (131) through a contact surface, and is not fixed by bolts.

6. The rocket-assisted rescue drone according to claim 5, characterized in that: A micro motor is installed in the innermost part of the cavity of the housing (131), and drives the telescopic section (132) to move via a ball screw; The housing (131) has a sweep angle of 60°, and the telescopic section (132) has no sweep angle; When the telescopic section 131 is extended, the fairing (133) is pushed open and away from the shell (131) so that the shell falls.

7. The rocket-assisted rescue drone according to claim 5, characterized in that: The housing (131) is an airfoil suitable for high-speed flight; The telescopic section (132) is an airfoil suitable for low-speed flight; The wingspan is increased by repeatedly nesting the telescopic mechanism composed of the outer shell (131) and the telescopic section (132) in multiple layers; A trailing edge rudder is provided at the trailing edge of the folding telescopic wing (13) to cooperate with the rudder (12) for attitude control.

8. The rocket-assisted rescue drone according to claim 1, characterized in that: The booster stage (3) has no attitude and track control equipment and is cylindrical in shape; The interstage section (2) is a round-to-square shell structure formed by splicing two halves of the structure, and the shells of the two halves are connected by explosive bolts; The interstage section (2) is connected to the cruise stage (1) and the booster stage (3) respectively located before and after the interstage section (2) by explosive bolts; The interstage section (2) is in a sloped shape, i.e., the front opening is small and the rear opening is large; The ratio of the length of the overall aircraft equipped with the rocket-assisted rescue drone to the diameter of the booster stage (3) is 12.

9. A control method for a rocket-assisted rescue drone according to any one of claims 1 to 8, characterized in that: include: Step S1: Active ascending stage; Step S2: passive ascending stage; Step S3: high-speed sliding section; Step S4: low-speed cruising section.

10. The rocket-assisted rescue drone according to claim 9, characterized in that: The step S1 includes: igniting the booster stage (3), accelerating the drone to take off, shutting down the booster stage (3), and separating the interstage (2); The step S2 includes: the cruise aircraft 1 continues to rise until it passes the highest point; The step S3 comprises: folding the telescopic wings (13) and unfolding them, and the cruise stage (1) gliding at high speed; The step S4 comprises: after the speed drops to a low speed, folding the telescopic wings (13) and extending the telescopic sections (132), jettisoning the air inlet fairing (18), and starting the turbojet engine (14); During the execution of steps S1 and S2, the foldable telescopic wings (13) are attached to both sides of the rectangular main shell (11); During the execution of step S3, the foldable and retractable wings (13) are rotated and unfolded to be perpendicular to the side of the main housing (11); During the execution of step S4, based on step S3, the telescopic section (132) is extended and the fairing (133) falls.

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