A small supersonic reusable multi-mission drone

Abstract

The invention relates to a small supersonic reusable multi-task UAV, comprising: an 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 isolation section, a gas generator unit, a combustion chamber, a nozzle and a propulsion control unit; the air inlet, the isolation 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.

Description

Technical Field

[0001] The invention relates to the field of aircraft, and in particular to a small supersonic reusable multi-task unmanned aerial vehicle. Background Art

[0002] Countries and regions such as the United States, Japan, and Europe have invested a lot of money, using low-signature signals, high-altitude, high-Mach number weapons as a breakthrough point, in order to gain an advantage and dominant position in the future.

[0003] UAVs are important combat and defense weapons and play an irreplaceable role in modern warfare. In particular, defense systems have an increasing demand for simulating low-signature signals and high-altitude, high-Mach-number intrusion targets.

[0004] Drones can simulate enemy aircraft or missile attacks during military exercises or weapon tests. The current small supersonic drones are consumables when simulating incoming targets. The Air Force, Navy, Army and other military services consume a lot of them in training every year. The small supersonic drones currently in use are disposable drones. They are scrapped after one use and cannot be reused, which is not economically cost-effective. In addition, the use scenario of a single drone is limited, and it is impossible to achieve flexible use in a wide airspeed range. Summary of the invention

[0005] The purpose of the present invention is to provide a small supersonic reusable multi-task UAV to solve the problem that small supersonic UAVs in the prior art have a single usage scenario and are not reusable.

[0006] To achieve the above-mentioned invention object, the present invention provides 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;

[0007] The main body of the drone adopts a waverider structure;

[0008] The propulsion system adopts a reusable integral solid ramjet engine, which includes: an air inlet, an isolation section, a gas generator unit, a combustion chamber, a nozzle and a propulsion control unit;

[0009] The air inlet, the isolation section, the combustion chamber and the nozzle are sequentially arranged along the symmetry axis of the UAV body; wherein 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;

[0010] The gas generator unit is arranged along the symmetry axis of the drone body and is detachably arranged in front of the combustion chamber;

[0011] The combustion chamber is provided with a solid rocket propellant of an integral solid ram engine;

[0012] The combustion chamber and the nozzle are detachably arranged.

[0013] According to one aspect of the present invention, the drone body is a hollow structure, which includes: a nose, a fuselage and a tail;

[0014] The machine head is a flat head;

[0015] The guidance system is arranged in the nose;

[0016] The propulsion system is arranged in the fuselage and the tail, wherein a first hatch that can be opened and closed is arranged at a position on the back of the fuselage corresponding to the gas generator unit.

[0017] According to one aspect of the present invention, the steering gear system comprises: a wing unit, a folding wing unit, a vertical tail unit and a steering gear control unit;

[0018] The wing unit is arranged on the fuselage;

[0019] The folding wing unit and the vertical tail unit are arranged on the tail.

[0020] According to one aspect of the present invention, the wing unit comprises: a wing and a wing servo for controlling the actuation of the wing;

[0021] The folding wing unit comprises: a horizontal wing, a wing retracting structure for controlling the retraction and extension of the horizontal wing, and a horizontal wing servo for controlling the actuation of the horizontal wing;

[0022] The vertical tail unit comprises: a vertical wing and a vertical tail servo for controlling the actuation of the vertical wing;

[0023] The wing servo, the wing retractable structure, the horizontal wing servo and the vertical tail servo are respectively connected to the servo control unit.

[0024] According to one aspect of the present invention, the wing retractable structure comprises: a fixed slide rail, a connecting / sliding rod, a folding wing connecting seat and a retractable drive device;

[0025] The slide rail, the connecting / sliding rod and the folding wing connecting seat are all long strip structures; wherein one end of the slide rail is rotatably connected to one end of the folding wing connecting seat;

[0026] The slide rail is provided with a slideway;

[0027] One end of the connecting / sliding rod is slidably connected to the slideway, and the other end is rotatably connected to the folding wing connecting seat;

[0028] The rotational connection position between the connecting / sliding rod and the folding wing connecting seat is spaced from the rotational connection position between the folding wing connecting seat and the sliding rail;

[0029] The retractable driving device is connected to the connecting / sliding rod and is used to drive the folding wing connecting seat to rotate;

[0030] The horizontal wing is rotatably connected to the folding wing connecting seat.

[0031] According to one aspect of the present invention, the landing system comprises: a front landing gear and a rear landing gear;

[0032] The front landing gear is arranged in the nose;

[0033] The rear landing gear is arranged in the fuselage, and in the direction from the nose to the tail, the rear landing gear is located behind the center of gravity of the small supersonic reusable multi-mission UAV;

[0034] The rear landing gear is symmetrically arranged with two of them, and is arranged in a three-point arrangement with the front landing gear;

[0035] A second door for retracting and unfolding the front landing gear is provided at a position of the nose corresponding to the front landing gear;

[0036] A third door for retracting and unfolding the rear landing gear is provided at a position of the fuselage corresponding to the rear landing gear.

[0037] According to one aspect of the present invention, it also includes: an external booster device;

[0038] The external booster device is detachably arranged on the tail.

[0039] According to one aspect of the present invention, when the UAV performs a high-altitude, high-Mach number mission, the UAV is dropped by a vehicle and the propulsion system of the UAV is directly used to complete the flight;

[0040] When the UAV performs a mid-altitude Mach number launch or a land / ship launch mission, the UAV is connected to the external booster and uses the external booster and the propulsion system in sequence to complete the flight; wherein the external booster is one of a booster rocket and a turbojet engine.

[0041] According to one aspect of the present invention, if the external booster device adopts a turbojet engine, the fuel supply system for the turbojet engine can be detachably installed inside the tail.

[0042] According to one solution of the present invention, the small supersonic reusable multi-task UAV of the present invention adopts a universal, serialized, and modular design to maximize interchangeability and universality.

[0043] According to one solution of the present invention, the aerodynamic design of the solution is excellent, ensuring that the aerodynamic characteristics of the drone are superior.

[0044] According to one solution of the present invention, a gas generator for generating fuel-rich gas is replaceable, which is convenient for replacement and effectively ensures multiple uses of the drone.

[0045] According to one solution of the present invention, the combustion chamber and the nozzle filled with solid rocket propellant are replaceable, which is convenient for replacement and effectively ensures the multiple uses of the drone.

[0046] According to one solution of the present invention, a landing gear system is provided, which effectively ensures the excellent recovery characteristics of the UAV.

[0047] According to one solution of the present invention, an external booster device is provided, which can facilitate the access of the external propulsion system, effectively improve the interchangeability and universality of the external propulsion system, and realize the multi-task use of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 is a front view schematically showing a small supersonic reusable multi-mission UAV according to one embodiment of the present invention;

[0049] Figure 2 is a schematic diagram schematically showing a small supersonic reusable multi-mission UAV system according to an embodiment of the present invention;

[0050] Figure 3 is a side view schematically showing a small supersonic reusable multi-mission UAV propulsion system according to one embodiment of the present invention;

[0051] Figure 4 is a schematic diagram showing the opening of the first door of a small supersonic reusable multi-mission UAV according to an embodiment of the present invention;

[0052] Figure 5 is a schematic diagram showing an opening diagram of a small supersonic reusable multi-mission UAV landing system according to an embodiment of the present invention;

[0053] Figure 6 is a structural diagram schematically showing a wing retractable structure according to an embodiment of the present invention;

[0054] Figure 7is a diagram schematically showing a horizontal wing in an extended state according to an embodiment of the present invention;

[0055] Figure 8 is a diagram schematically showing a retracted state of a horizontal wing according to an embodiment of the present invention;

[0056] Fig. 9 is a diagram schematically showing a connection between a small supersonic reusable multi-mission UAV and an external booster device according to an embodiment of the present invention;

[0057] Fig.10 The figure schematically shows a connection diagram between a small supersonic reusable multi-mission UAV and an external booster device according to another embodiment of the present invention. DETAILED DESCRIPTION

[0058] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0059] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0060] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0061] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, according to one embodiment of the present invention, a small supersonic reusable multi-task UAV of the present invention comprises: a UAV body 1, a guidance system 2, a propulsion system 3, a steering gear system 4, a landing system 5 and a flight control system arranged in the UAV body 1. In this embodiment, the UAV body 1 adopts a waverider structure. In this embodiment, the propulsion system 3 adopts a reusable integral solid ramjet engine, which comprises: an air inlet 31, an isolation section 32, a gas generator unit 33, a combustion chamber 34, a nozzle 35 and a propulsion control unit; the air inlet 31, the isolation section 32, the combustion chamber 34 and the nozzle 35 are arranged in sequence along the symmetry axis of the UAV body 1; wherein the air inlet of the air inlet 31 is located at the abdomen of the UAV body 1, and the nozzle of the nozzle 35 is located at the tail of the UAV body 1. In this embodiment, the gas generator unit 33 is arranged along the symmetry axis of the UAV body 1, and is detachably arranged in front of the combustion chamber 34. In this embodiment, the combustion chamber 34 is provided with solid rocket propellant of the integral solid ramjet engine. In this embodiment, the combustion chamber 34 and the nozzle 35 can be directly disassembled along the direction of the tail 13, so as to facilitate direct replacement of the combustion chamber 34 and the nozzle 35.

[0062] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the drone body 1 is a hollow structure, which includes: a nose 11, a fuselage 12 and a tail 13; wherein the nose 11 is a flat head; and the guidance system 2 is arranged in the nose 11. In this embodiment, the propulsion system 3 is arranged in the fuselage 12 and the tail 13, wherein a first hatch 12a that can be opened and closed is arranged at a position corresponding to the gas generator unit 33 on the back of the fuselage 12.

[0063] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the servo system 4 includes: a wing unit 41, a folding wing unit 42, a vertical tail unit 43 and a servo control unit. In this embodiment, the wing unit 41 is arranged on the fuselage 12, and the wing unit 41 is arranged on two opposite sides of the fuselage 12 in the horizontal direction. In this embodiment, the folding wing unit 42 and the vertical tail unit 43 are arranged on the tail 13, wherein the folding wing unit 42 is arranged on two opposite sides of the fuselage 12 in the horizontal direction, and two vertical tail units 43 are arranged at intervals on the back of the tail 13. In this embodiment, the roll control surface of the whole machine is formed by the wing unit 41, the pitch control surface of the whole machine is formed by the folding wing unit 42, and the yaw control surface is formed by the vertical tail unit 43.

[0064] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the wing unit 41 includes: a wing 411 and a wing servo for controlling the actuation of the wing 411. In this embodiment, the folding wing unit 42 includes: a horizontal wing 421, a wing retracting structure 422 for controlling the retraction of the horizontal wing 421, and a horizontal wing servo for controlling the actuation of the horizontal wing 421.

[0065] In this embodiment, the vertical tail unit 43 includes a vertical wing 431 and a vertical tail servo for controlling the movement of the vertical wing 431 .

[0066] In this embodiment, the wing servo, the wing retractable structure 422, the horizontal wing servo and the vertical tail servo are respectively connected to the servo control unit.

[0067] Through the above arrangement, the present invention realizes a tailless design, and effectively enhances the controllability of the whole machine through the design of the winglets, and can conveniently realize lateral and rolling control.

[0068] Combination Figure 5 , Figure 6 and Figure 7 As shown, according to one embodiment of the present invention, the wing retractable structure 422 includes: a fixed slide rail 422a, a connecting / sliding rod 422b, a folding wing connecting seat 422c and a retractable driving device. In this embodiment, the slide rail 422a, the connecting / sliding rod 422b and the folding wing connecting seat 422c are all long strip structures; wherein one end of the slide rail 422a is rotatably connected to one end of the folding wing connecting seat 422c. In this embodiment, the slide rail 422a is arranged perpendicular to the axial direction of the drone body 1, and a slideway 422a1 is arranged on the slide rail 422a; one end of the connecting / sliding rod 422b is slidably connected to the slideway 422a1, and the other end is rotatably connected to the folding wing connecting seat 422c. In this embodiment, the rotational connection position of the connecting / sliding rod 422b and the folding wing connecting seat 422c is arranged at an interval from the rotational connection position of the folding wing connecting seat 422c and the slide rail 422a. In this embodiment, the retractable drive device is connected to the connecting / sliding rod 422b to drive the folding wing connecting seat 422c to rotate. In this embodiment, the horizontal wing 421 is rotatably connected to the folding wing connecting seat 422c, and the rotation control of the horizontal wing 421 is realized through the horizontal wing steering gear.

[0069] In this embodiment, the retracting and extending driving device is implemented by a motor or a hydraulic machine.

[0070] Combination Figure 1 , Figure 2 , Figure 3 and Figure 8 As shown, according to one embodiment of the present invention, the landing system 5 includes: a front landing gear 51 and a rear landing gear 52. In this embodiment, the front landing gear 51 is arranged in the nose 11; the rear landing gear 52 is arranged in the fuselage 12, and along the direction from the nose 11 to the tail 13, the rear landing gear 52 is located behind the center of gravity of the small supersonic reusable multi-task UAV. In this embodiment, two rear landing gears 52 are symmetrically arranged, and are arranged in a three-point manner with the front landing gear 51. In this embodiment, a second door 11a for retracting and releasing the front landing gear 51 is arranged at a position of the nose 11 corresponding to the front landing gear 51, and a third door 12b for retracting and releasing the rear landing gear 52 is arranged at a position of the fuselage 12 corresponding to the rear landing gear 52.

[0071] Through the above arrangement, the landing system 5 can play a role of stable support during the landing, taxiing and parking of the UAV, while absorbing the vibration of the UAV during taxiing and landing.

[0072] like Fig. 9 , Fig.10 As shown, according to one embodiment of the present invention, a small supersonic reusable multi-task UAV of the present invention further includes: an external booster device a; the external booster device a is arranged on the tail 13, and the external booster device a is detachably connected to the tail 13. In this embodiment, when the UAV performs a high-altitude high Mach number mission (i.e. fighter launch), no external boost is required, and the UAV propulsion system 3 is directly used to complete the flight, that is, the solid rocket boost in the combustion chamber provides the power for autonomous flight after delivery; when the UAV performs a mid-altitude Mach number launch or land / ship launch mission, the UAV is connected to the external booster device (a), and the external booster device a and the propulsion system 3 are used in sequence to complete the flight; in this embodiment, the external booster device a is one of a booster rocket (bomber launch) and a turbojet engine (ship launch / land launch). In this embodiment, the UAV of the present invention can be boosted by directly using the solid rocket in the combustion chamber according to different mission requirements; or the external booster device a connected to the external booster device a can be used to achieve boost acceleration to the relay Mach number of the UAV, and then the solid rocket of the UAV itself is relay-ignited; the UAV is accelerated to the starting Mach number of the ramjet engine, the gas generator 33 is relay-ignited, and the rich fuel gas is supplementally burned in the combustion chamber, so that the aircraft is accelerated to the cruising Mach number and performs maneuvering flight; finally, after the UAV completes the flight mission, it is guided by the guidance system 2 to glide to the vicinity of the recovery point, and the terminal landing system 5 is activated to achieve landing recovery.

[0073] In this embodiment, when a fighter jet is used for launching (high altitude and high Mach launch), no external booster is required, and the solid rocket in the combustion chamber of the drone is directly used for boosting, accelerating to the ramjet start-up Mach number, and the combustion chamber forms a post-combustion chamber cavity as the solid rocket booster is completely burned. The gas generator 33 is ignited in relay, and the rich fuel gas is post-combusted in the combustion chamber, so that the aircraft is accelerated to the cruising Mach number and performs maneuvering flight.

[0074] In this embodiment, when the bomber is launched, the external booster device a uses a booster rocket, and the bomber launches the rocket-boosted UAV from the Mach number (such as 8km, Ma0.8) in the air. The booster rocket can be modularly installed on the tail 13 of the UAV. The UAV after the solid rocket booster is installed is as follows: Fig. 9 As shown, the UAV is pushed to the UAV relay height and Mach number (high altitude and high Mach number) by the booster rocket, and then the booster rocket module is separated from the UAV, and the UAV starts to work. Its working process is consistent with the above process, and will not be repeated here.

[0075] like Fig.10 As shown, according to one embodiment of the present invention, when the external booster a is a turbojet engine, the fuel supply system (i.e., oil bag or oil storage tank) of the turbojet engine can be detachably arranged in the cabin inside the tail 13, and then connected to the turbojet engine through a supply pipeline. The turbojet engine controller and the fuel supply system controller are respectively connected to the controlled components and the drone as a whole through corresponding cables. Through the turbojet booster, the drone is pushed to the relay height and Mach number (high altitude high Mach number), and then the external booster a is separated from the drone, and the drone starts to work. In this embodiment, the turbojet engine is installed on the back of the drone tail 13, and a recovery device (such as a parachute) is provided on the turbojet engine, and effective recovery can be achieved after the turbojet engine is detached.

[0076] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

[0077] The above is only one solution of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A small supersonic reusable multi-mission UAV, characterized in that: include: An unmanned aerial vehicle body (1), a guidance system (2), a propulsion system (3), a steering gear system (4), a take-off and landing system (5), and a flight control system arranged in the unmanned aerial vehicle body (1); The drone body (1) adopts a waverider structure; The propulsion system (3) adopts a reusable integral solid ramjet engine, which comprises: an air inlet (31), an isolation section (32), a gas generator unit (33), a combustion chamber (34), a nozzle (35) and a propulsion control unit; The air inlet (31), the isolation section (32), the combustion chamber (34) and the nozzle (35) are sequentially arranged along the axis of symmetry of the drone body (1); wherein the air inlet of the air inlet (31) is located at the belly of the drone body (1), and the nozzle of the nozzle (35) is located at the tail of the drone body (1); The gas generator unit (33) is arranged along the symmetry axis of the drone body (1), and is detachably arranged in front of the combustion chamber (34); The combustion chamber (34) is provided with solid rocket propellant of the integral solid ramjet engine; The combustion chamber (34) and the nozzle (35) are detachably arranged.

2. The small supersonic reusable multi-mission UAV according to claim 1, characterized in that: The drone body (1) is a hollow structure, comprising: a nose (11), a fuselage (12) and a tail (13); The machine head (11) is a flat head; The guiding system (2) is arranged in the machine head (11); The propulsion system (3) is arranged in the fuselage (12) and the tail (13), wherein a first hatch (12a) that can be opened and closed is arranged at a position on the back of the fuselage (12) corresponding to the gas generator unit (33).

3. The small supersonic reusable multi-mission UAV according to claim 2, characterized in that: The steering gear system (4) comprises: a wing unit (41), a folding wing unit (42), a vertical tail unit (43) and a steering gear control unit; The wing unit (41) is arranged on the fuselage (12); The folding wing unit (42) and the vertical tail unit (43) are arranged on the tail (13).

4. The small supersonic reusable multi-mission UAV according to claim 3, characterized in that: The slat unit (41) comprises: a slat (411) and a slat servo for controlling the movement of the slat (411); The folding wing unit (42) comprises: a horizontal wing (421), a wing retracting and extending structure (422) for controlling the retraction and extension of the horizontal wing (421), and a horizontal wing steering gear for controlling the actuation of the horizontal wing (421); The vertical tail unit (43) comprises: a vertical wing (431) and a vertical tail servo for controlling the movement of the vertical wing (431); The wing servo, the wing retractable structure (422), the horizontal wing servo and the vertical tail servo are respectively connected to the servo control unit.

5. The small supersonic reusable multi-mission UAV according to claim 4, characterized in that: The wing retractable structure (422) comprises: a fixed slide rail (422a), a connecting / sliding rod (422b), a folding wing connecting seat (422c) and a retractable driving device; The slide rail (422a), the connecting / sliding rod (422b) and the folding wing connecting seat (422c) are all long strip structures; wherein one end of the slide rail (422a) is rotatably connected to one end of the folding wing connecting seat (422c); The slide rail (422a) is provided with a slideway (422a1); One end of the connecting / sliding rod (422b) is slidably connected to the slideway (422a1), and the other end is rotationally connected to the folding wing connecting seat (422c); The rotational connection position between the connecting / sliding rod (422b) and the folding wing connecting seat (422c) and the rotational connection position between the folding wing connecting seat (422c) and the sliding rail (422a) are spaced apart; The retractable driving device is connected to the connecting / sliding rod (422b) and is used to drive the folding wing connecting seat (422c) to rotate; The horizontal wing (421) is rotatably connected to the folding wing connecting seat (422c).

6. The small supersonic reusable multi-mission UAV according to claim 5, characterized in that: The landing system (5) comprises: a front landing gear (51) and a rear landing gear (52); The front landing gear (51) is arranged in the nose (11); The rear landing gear (52) is arranged in the fuselage (12), and along the direction from the nose (11) to the tail (13), the rear landing gear (52) is located behind the center of gravity of the small supersonic reusable multi-mission UAV; The rear landing gear (52) is symmetrically arranged in two pieces and is arranged in a three-point arrangement with the front landing gear (51); A second door (11a) for retracting and unfolding the front landing gear (51) is provided at a position of the nose (11) corresponding to the front landing gear (51); A third door (12b) for retracting and unfolding the rear landing gear (52) is provided at a position of the fuselage (12) corresponding to the rear landing gear (52).

7. The small supersonic reusable multi-mission UAV according to claim 6, characterized in that: Also includes: External booster device (a); The external booster device (a) is detachably arranged on the tail (13).

8. The small supersonic reusable multi-mission UAV according to claim 7, characterized in that: When the UAV performs a high-altitude, high-Mach-number mission, the UAV is dropped by a vehicle and the propulsion system (3) of the UAV is directly used to complete the flight; When the UAV performs a mid-air Mach number launch or a land / ship launch mission, the UAV is connected to the external booster device (a), and uses the external booster device (a) and the propulsion system (3) in sequence to complete the flight; wherein the external booster device (a) is one of a booster rocket and a turbojet engine.

9. The small supersonic reusable multi-mission UAV according to claim 8, characterized in that: If the external booster device (a) is a turbojet engine, the fuel supply system for the turbojet engine can be detachably installed inside the tail (13).

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