CN113386960A

CN113386960A - Small-size target unmanned vehicles in high maneuvering wide-speed area

Info

Publication number: CN113386960A
Application number: CN202010166579.4A
Authority: CN
Inventors: 甘文彪
Original assignee: Beijing Techx Technology Co ltd
Current assignee: Beijing Techx Technology Co ltd
Priority date: 2020-03-11
Filing date: 2020-03-11
Publication date: 2021-09-14

Abstract

The invention provides a high-maneuvering wide-speed-range target unmanned aerial vehicle. The aircraft comprises: the two fixed main wings are arranged on two sides of the machine body, and the pair of V-shaped tail wings are arranged at the tail part of the machine body; the fixed main wing adopts a supercritical wing type, so that the aerodynamic performance of the unmanned aerial vehicle in a transonic speed range can be improved; the V-shaped empennage is provided with distributed control surfaces, and the V-shaped empennage can play the roles of a rudder and a lifting rudder by the mutual matching of the control surfaces; by adopting the small V-shaped tail with the distributed control surfaces and the supercritical fixed main wing, the unmanned aerial vehicle has higher maneuverability to meet the requirements of different types of flight tasks.

Description

Small-size target unmanned vehicles in high maneuvering wide-speed area

Technical Field

The embodiment of the invention relates to an aircraft technology, in particular to a small target unmanned aircraft with high maneuvering and wide speed range.

Background

Target unmanned vehicles are often used to verify the systematic tactical technical performance of weapons, and are an alternative to target for anti-aircraft weapons. With the development of modern aircrafts, the requirements on the speed range and the maneuverability of the target unmanned aircraft are higher and higher.

In actual use, the target unmanned aerial vehicle is required to carry different task loads according to different task requirements, and light, electricity and infrared signal characteristics of corresponding targets and flight speed and maneuvering capacity of the corresponding targets are simulated to check the guidance and fight coordination of the missile warhead. With the development of the technology, the performance of the supposed target aircraft is greatly improved, the subsonic speed is gradually transited to the transonic speed and even the supersonic speed, and meanwhile, the maneuvering performance of the modern aircraft is stronger and stronger due to the increasingly advanced control and transmission system. In order to better simulate the flight state of a hypothetical target, a brand-new design needs to be provided for a target unmanned aerial vehicle so as to break through the limitation of the traditional airfoil design in the transonic speed range and the limitation of the layout of a transmission control surface on the maneuverability of the target unmanned aerial vehicle. The supercritical wing profile can delay the phenomenon of sharp increase of the resistance of the wing when approaching the speed of sound, can effectively improve the critical Mach number of the aircraft, and is mainly used for civil airliners and large-scale transport planes at present. Under the condition of control surface distribution and mutual cooperation of the distributed V-shaped tail rudder surfaces, the control of transverse and longitudinal decoupling and coupling can be realized, and the control capability of the aircraft is superior to that of the conventional tail wing layout. The two combined high-maneuvering wide-speed-range target unmanned aerial vehicle can be used for better simulating the flight characteristics of a hypothetical target.

Disclosure of Invention

The invention provides a high-maneuverability wide-speed-range target unmanned aerial vehicle which can carry various loads, simulate the flight state of a transonic-speed-range aircraft, and has higher maneuverability, so that the target unmanned aerial vehicle has stronger simulation capability on an imaginary target.

The invention provides a high-maneuvering wide-speed-range target unmanned aerial vehicle, which comprises:

the aircraft comprises an aircraft body capable of carrying various loads, two supercritical fixed main wings arranged on two sides of the aircraft body, and two distributed control surface V-shaped empennages arranged on two sides of the tail of the aircraft body.

The aircraft body can carry multiple loads, and the anterior segment is the load cabin, can carry corresponding load according to the simulation task needs, and well anterior segment is the parachute cabin, installs the parachute package and is convenient for retrieve unmanned vehicles, and well back end is the oil tank, and the back end is the engine compartment.

The supercritical fixed main wings are symmetrically arranged at the middle section of the body along the longitudinal direction of the body, the supercritical wing type design is adopted, and a pair of ailerons are symmetrically arranged at the rear edges of the outer sides of the two main wings.

The two tail wings are symmetrically arranged at the rear section of the engine body along the longitudinal direction of the engine body, and two pairs of distributed control surfaces are symmetrically arranged at the rear edges of the two tail wings along the spanwise direction.

The supercritical fixed main wing is a trapezoidal wing with a sweepback angle not exceeding 30 degrees.

Optionally, the main wing is mounted on the fuselage in a position of an upper single wing, a middle single wing or a lower single wing.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It is to be understood that the drawings in the following description are of some embodiments of the invention, and are intended to provide further understanding of the invention and are not to be construed as limiting the invention.

Fig. 1 is a schematic diagram of a high-maneuvering wide-speed-range target unmanned aerial vehicle provided by an embodiment of the invention.

Fig. 2 is a schematic diagram of a supercritical airfoil main wing of a target unmanned aerial vehicle with high maneuvering wide speed range according to an embodiment of the invention.

Fig. 3 is a schematic diagram of a small V-shaped tail wing with distributed control surfaces of a target unmanned aerial vehicle with high maneuvering and wide speed ranges, provided by an embodiment of the invention.

Fig. 4 is a schematic flight envelope diagram of a high-maneuvering wide-speed-range target unmanned aerial vehicle provided by an embodiment of the invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It should be understood that the detailed description and specific examples, while indicating the present invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.

The high-maneuvering wide-speed-range target unmanned aerial vehicle provided by the embodiment mainly comprises: the airplane comprises an airplane body (comprising a front section 1, a middle front section 2, a middle rear section 3 and a rear section 4), wings 5, a tail wing 6, ailerons 7 and an engine 8.

The fuselage is divided into anterior segment 1, well anterior segment 2, well back end 3, back end 4, four parts, and adjacent intersegmental adoption compartment divides. As shown in fig. 1, a front section 1 of the body is used for installing airborne electronic equipment and task loads required by tasks, a middle front section 2 is used for installing parachute bags, a middle rear section 3 is used for installing an oil tank, and a rear section 4 is used for installing a navigation/flight control system and a power system (engine).

Optionally, the cross section of the machine body is elliptical, so that the machine body with the elliptical cross section has a smaller surface area under the same machine body volume, and further the friction resistance of the machine body is smaller. If the elliptical cross section is not adopted due to some special conditions, other cross section shapes can be selected, and the cross section shape of the machine body is not limited in the embodiment.

Optionally, the fuselage skin can be made of carbon fiber materials, so that the whole weight of the fuselage is effectively reduced while the bearing capacity of the fuselage is enhanced. The structural framework of the machine body mainly comprises an aluminum frame, an aluminum reinforcing frame and an aluminum stringer; the device such as task load, power is installed to organism anterior segment 1, and anterior segment 2 is the parachute cabin in the organism, installs the parachute package, and back end 3 is the oil tank in the organism, and organism back end 4 can be according to task needs installation engine and navigation/flight control system or airborne equipment etc..

The wing 5 is used for providing lift force for the unmanned aerial vehicle in the flat flight process, as shown in fig. 1 and fig. 2, the wing section is designed to be a supercritical wing type, the front edge is blunt and round, the upper surface is flat, the rear edge is concave, the rear loading of the wing section is formed, the shock wave strength in the transonic speed flight process can be effectively reduced, and the aerodynamic performance of the unmanned aerial vehicle in the transonic speed range is improved. The geometry is trapezoidal with a maximum sweep angle of no more than 30 deg..

The tail fin 6 is a V-shaped fin, and has functions of a vertical fin and a horizontal fin, and the generated interference resistance is low. As shown in fig. 1 and 3, two pairs of distributed control surfaces are arranged on the tail wing in the spanwise direction, each control surface 9 is controlled by an independent steering engine 10, and the control surfaces can be distributed and matched with each other to realize transverse and longitudinal decoupling and coupling control.

Optionally, in the small-sized high-mobility wide-speed-range target unmanned aerial vehicle provided by the embodiment of the invention, a rocket boosting mode can be adopted in a takeoff phase, and a parachute landing mode can be adopted for recovery. The recovery system is composed of an umbrella opening mechanism, a main umbrella, a falling joint and the like, wherein the parachute is a circular parachute and is arranged in the front section 2 of the machine body.

According to the target unmanned aerial vehicle with high maneuvering and wide speed range, as shown in fig. 4, under the condition of normal weight takeoff not exceeding 100 kg, the conditions of boost takeoff and overload flight are considered, and the lifting limit of the target unmanned aerial vehicle provided by the embodiment of the invention is not less than 6500 m.

Finally, it should be noted that: the above embodiments are merely illustrative of the technical solutions of the present invention, and not restrictive; although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that the present invention may be practiced without modification of the foregoing embodiments or with equivalents of some or all of their features; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A high maneuvering wide speed range small target unmanned aerial vehicle, comprising: two supercritical fixed main wings arranged on two sides of the machine body; the small V-shaped tail is arranged at the tail of the machine body and provided with a distributed control surface; and when the total weight is not more than 100 kilograms, the aircraft can fly in a speed range of 0.1-0.8 Mach.

2. The two fixed main wings arranged on two sides of the machine body according to claim 1 are characterized in that the aspect ratio is 7-9, a supercritical wing type is adopted, the geometric shape of the supercritical wing type is a trapezoidal wing with a maximum backswept angle not exceeding 30 degrees, the front edge of the wing type is blunt and round, the upper surface is flat, the rear edge of the wing type is concave, the rear loading of the wing type is formed, the shock wave strength during transonic speed flight can be effectively reduced, and the aerodynamic performance of the unmanned aerial vehicle in the transonic speed range is improved.

3. The small V-tail arranged on the tail part of the machine body as claimed in claim 1, wherein the small V-tail is provided with two pairs of distributed control surfaces which are distributed on the rear sections of the two V-shaped tail wings along the spanwise direction, and the distributed control surfaces can be distributed and matched with each other through the control surfaces to play a role in decoupling control of a rudder and an elevator of an aircraft.