CN116022325A - Folding storage type variant aircraft - Google Patents

Abstract

The invention provides a folding and accommodating type variant aircraft, which comprises the following components: the device comprises a front body, a rear body, wings, tail wings, a propeller, a turnover mechanism and a cylinder; wherein the front machine body is connected with the rear machine body through a turnover mechanism; the front machine body is attached to the rear machine body after being turned 180 degrees; the wings are symmetrically arranged on two sides of the turnover mechanism, the wings are connected with the front fuselage by adopting oblique rotating shafts, and the wings are axially parallel to the rear fuselage after being rotationally folded; the screw propeller is arranged at the tail end part of the rear fuselage, and the tail wing is arranged at the rear part of the rear fuselage; the wing comprises a plurality of wing segments; the wing folding device is arranged at the joint of each wing section of the wing, so that the wing span direction and the chord direction have a multi-section folding function; the aircraft is folded and then is accommodated in the cylinder. The invention has the advantages of large span, high lift-drag ratio, ultra-long endurance, quick remote delivery and the like.

Description

Folding storage type variant aircraft

Technical Field

The invention relates to a folding storage type variant aircraft, and belongs to the technical field of unmanned aerial vehicles.

Background

The traditional fixed-wing aircraft with large aspect ratio can take off and land under the condition of better airport guarantee, has stricter requirements on weather conditions, influences the application effect of the aircraft, and needs to be folded and stored in a cylinder with smaller diameter so as to be convenient to carry and transport in order to improve the quick maneuvering deployment capability and all-weather standby capability of the fixed-wing aircraft. At present, a wide area reconnaissance monitoring unmanned aerial vehicle is commonly developed in university of Ma province and NASA Drepad laboratory, and the span of the unmanned aerial vehicle after unfolding is 1.27 m. The FLYRT unmanned aerial vehicle developed by the American naval research center is a small unmanned aerial vehicle capable of being launched by a carrier-based gun, the unmanned aerial vehicle wing is 5.5m in length and 1.6m in length, the unmanned aerial vehicle can fly for 20 minutes at the speed of 102-130km/h, after being launched, the cross tail is ejected by a spring to operate, after the solid rocket is burned out, the rocket propulsion part is abandoned by the aircraft, the folding wing and the antenna are unfolded, and the unmanned aerial vehicle enters a complete working state under the driving of a motor. However, the wingspan of the existing folding aircraft is smaller, and the storage proportion is not high. Under such a technical background, a folding storage type unmanned aerial vehicle is proposed.

Disclosure of Invention

The technical solution of the invention is as follows: the utility model provides a solve the not enough of prior art, provide a many times multiple folding mode mixed use's accomodate formula variant aircraft, make the aircraft can accomodate in the space of less diameter and length according to great shrink proportion to unmanned aerial vehicle's long-range delivery and transportation. The unmanned aerial vehicle folded in the mode has the advantages of large span, high lift-drag ratio, ultra-long endurance, quick remote delivery and the like.

The technical scheme of the invention is as follows:

a folding stowable variant aircraft comprising: the device comprises a front body, a rear body, wings, tail wings, a propeller, a turnover mechanism and a cylinder; wherein the front machine body is connected with the rear machine body through a turnover mechanism; the front machine body is jointed with the rear machine body after being turned over; the wings are symmetrically arranged on two sides of the turnover mechanism, the wings are connected with the front fuselage by adopting oblique rotating shafts, and the wings are axially parallel to the rear fuselage after being rotationally folded; the screw propeller is arranged at the tail end part of the rear fuselage, and the tail wing is arranged at the rear part of the rear fuselage; the wing comprises a plurality of wing segments; the wing folding device is arranged at the joint of each wing section of the wing, so that the wing span direction and the chord direction have a multi-section folding function; the aircraft is folded and then is accommodated in the cylinder.

In the variant aircraft, the wing folding device comprises a wing hinge, an actuating device and a locking device, so that v-type, z-type and w-type folding is realized.

In the variant aircraft, each wing section consists of a front edge, a wing box and a rear edge, and the front edge, the wing box and the rear edge are connected through an actuating mechanism and a locking mechanism to realize folding.

In the above-described modified aircraft, the tail wing includes two tail surfaces and a root shaft, and the tail surfaces are rotatably unfolded into a state perpendicular to the rear fuselage by the root shaft.

In the above-mentioned variant aircraft, the propeller includes two foldable blades, and the folded propeller is unfolded into a vertical rear fuselage state by centrifugal force generated by rotation of the motor; the foldable blade has a function of folding forward or backward.

In the above variant aircraft, the wing has a large aspect ratio.

In the variant aircraft, the cylinder body is in a split configuration of the cylindrical shell, and the aircraft is restrained in the cylinder body after being retracted, so that the aircraft is prevented from being damaged in the delivery process.

In the modified aircraft, each part of the wing in the folded state is rotated to be perpendicular to the fuselage from a state parallel to the fuselage in the folded state by rotating around the root axis of the wing.

In the variant aircraft, the wing front edge, the wing box and the rear edge are also moved from the slotting folding state to the complete splicing state through the actuating mechanism and the locking mechanism when the wing is unfolded in a rotating mode.

In the above-described variant aircraft, the front end portion of the front fuselage is provided with a protruding portion, the rear end portion of the rear fuselage is provided with a constricted portion, and the protruding portion is engaged with the constricted portion.

The beneficial effects of the invention compared with the prior art are as follows:

(1) The invention can be used for expanding a long-endurance unmanned plane with a large span and a large aspect ratio in a small column space in a shrinkage way, thereby improving the capabilities of remote delivery, burst prevention and the like of the plane.

(2) The invention designs a whole set of airplane folding and unfolding form and airplane configuration, and the airplane is unfolded to be in a conventional layout form;

(3) The invention designs a whole set of airplane folding and unfolding form and airplane configuration, and the airplane can be efficiently stored in a cylindrical barrel after being folded, so that the shrinkage ratio is extremely high.

Drawings

FIG. 1 is a schematic view of a cartridge of the present invention;

fig. 2 is a schematic view of a folding state of the unmanned aerial vehicle according to the present invention;

FIG. 3 is a schematic view of the wing rotational deployment process of the present invention; (a) is in a wing rotating and folding state, (b) is in a wing rotating and unfolding process, and (c) is completed in the wing rotating and unfolding process;

FIG. 4 is a schematic illustration of the wing fold and unfold process of the present invention; (a) is in a wing folding state, (b) is in a wing folding and unfolding completion state, and (c) is in a wing folding and unfolding completion state;

FIG. 5 is a schematic view of the fuselage deployment process of the present invention; (a) In the unfolded state of the airframe, (b) in the unfolded state of the airframe;

FIG. 6 is a schematic view of the tail rotor deployment process of the present invention;

fig. 7 is a schematic structural diagram of the unmanned aerial vehicle of the present invention.

Detailed Description

The present invention is described in further detail below with reference to the drawings and detailed description.

The invention discloses a folding storage type variant aircraft, which comprises the following components: the device comprises a front body 1, a rear body 2, wings, tail wings, a propeller, a turnover mechanism and a cylinder body; wherein the front machine body 1 and the rear machine body 2 are connected through a turnover mechanism; the front machine body is attached to the rear machine body 2 after being turned 180 degrees; the wings are symmetrically arranged on two sides of the turnover mechanism, the wings are connected with the front fuselage 1 by adopting oblique rotating shafts, and the wings are axially parallel to the rear fuselage 2 after being rotationally folded; the screw propeller 13 is arranged at the tail end of the rear fuselage 2, and the tail wing is arranged at the rear part of the rear fuselage 2; the wing comprises a plurality of wing segments; the wing folding device is arranged at the joint of each wing section of the wing, so that the wing span direction and the chord direction have a multi-section folding function; the aircraft is folded and then is accommodated in the cylinder. The wing folding device comprises a wing hinge, an actuating device and a locking device, and realizes v-type, z-type and w-type folding. Each wing section consists of a front edge, a wing box and a rear edge, and the front edge, the wing box and the rear edge are connected through an actuating mechanism and a locking mechanism to realize folding.

The high-proportion storage of the unmanned aerial vehicle is completed through the integral sweepback folding of the half wing, the multi-section overturning folding of the wing in the wingspan direction, the three-section folding of the wing in the chord length direction, the overturning folding of the two sections of the fuselage, the forward sweepback folding v-shaped tail wing and the comprehensive application of the propeller folding.

Fig. 1 is a cylinder view of an aircraft for stowing after folding. The cylinder 14 is in a cylindrical shell split configuration, and is divided into two halves, and the aircraft is restrained in the cylinder 14 after being retracted, so that the aircraft can be prevented from being damaged in the delivery process.

Fig. 2 is a state diagram of the separation of the barrel 14 into two pieces and the aircraft, the barrel 14 falls down after being separated from the aircraft, and the folded aircraft wings are tightly restrained in the cylindrical barrel envelope after being folded for many times, wherein the inner wing front edge 3, the inner wing box 4, the inner wing rear edge 5, the secondary outer wing front edge 6, the secondary outer wing box 7, the secondary outer wing rear edge 8, the outer wing front edge 9, the outer wing box 10, the outer wing rear edge 11, the front fuselage 1, the rear fuselage 2, the tail wing 12 and the propeller blades 13 are all in a folded state. The leading edge, the wing box and the trailing edge are in a slotted and folded state to meet the cylinder envelope of the cylinder 14.

Fig. 3 (a), 3 (b) and 3 (c) show the wing rotating and unfolding process, and each part of the wing in the folded state is rotated to be perpendicular to the body from the parallel state with the body in the folded state by rotating around the root rotating shaft of the wing.

Fig. 4 (a) shows a wing rotation and unfolding completion state, and the front edge, the wing box and the rear edge of the wing are moved from a slotting folding state to a complete splicing state through an actuating mechanism and a locking mechanism while rotating and unfolding.

The inner wing comprises a front edge 3, an inner wing box 4 and an inner wing rear edge 5; the secondary outer wing comprises a secondary outer wing leading edge 6, a secondary outer wing box 7 and a secondary outer wing trailing edge 8; the outer wing comprises an outer wing leading edge 9, an outer wing box 10, an outer wing trailing edge 11.

Fig. 4 (b) shows the wing fold and unfolding process, in which the multi-layer folded wing is gradually unfolded to a horizontal state by means of hinges and actuators between wing sections.

Fig. 4 (c) shows the wing folding and unfolding completed state, and after the wing folding and unfolding is completed, the connecting surfaces of all sections of the wing are locked by an automatic locking device, so that the wing with large wingspan which can reliably bear force is formed.

Fig. 5 (a) shows a state of the body turning and folding process, in which the front body 1 in the folded state is turned forward by a hinge and an actuation mechanism between the front body 1 and the rear body 2 to form a completed body state.

Fig. 5 (b) shows the front body 1 in a folded state, the front body 1 is unfolded and automatically locked, it can be seen that the front body 1 and the rear body 2 are required to be designed into a shape suitable for storage, the front end of the front body 1 is provided with a protruding portion, the rear end of the rear body 2 is provided with a shrinking portion, and the protruding portion is matched with the shrinking portion.

Fig. 6 is a state diagram showing the development process of the tail vane 12 and the folding propeller 13, the tail vane comprises two tail vane surfaces 12 and a root rotating shaft, and the tail vane surfaces 12 are unfolded into a state of being vertical to the rear fuselage 2 through the rotation of the root rotating shaft. The propeller comprises two foldable blades 13, and the folded propeller 13 is unfolded into a state of being vertical to the rear machine body 2 through centrifugal force generated by rotation of a motor; the foldable blade 13 has a function of folding forward or backward.

Fig. 7 is a state diagram showing the tail wing 12 and the propeller 13 in a fully deployed state, and the fully deployed aircraft has an elongated fuselage, a high aspect ratio wing, and is a conventional layout form of an ultra-long-endurance unmanned aircraft.

While the invention has been described in terms of the preferred embodiments, it is to be understood that the invention is not limited thereto, but is capable of modification and substitution which will occur to those skilled in the art within the scope of the invention.

What is not described in detail in the present specification belongs to the known technology of those skilled in the art.

Claims (10)

1. A folding stowable variant aircraft, comprising: the device comprises a front fuselage (1), a rear fuselage (2), wings, tail wings, a propeller, a turnover mechanism and a barrel; wherein, the front machine body (1) and the rear machine body (2) are connected through a turnover mechanism; the front machine body (1) is attached to the rear machine body (2) after being overturned; the wings are symmetrically arranged on two sides of the turnover mechanism, the wings are connected with the front fuselage (1) through oblique rotating shafts, and the wings are axially parallel to the rear fuselage (2) after being rotationally folded; the screw propeller (13) is arranged at the tail end of the rear machine body (2), and the tail wing is arranged at the rear part of the rear machine body (2); the wing comprises a plurality of wing segments; the wing folding device is arranged at the joint of each wing section of the wing, so that the wing span direction and the chord direction have a multi-section folding function; the aircraft is folded and then is accommodated in the cylinder.

2. A folding stowable variant aircraft according to claim 1, wherein: the wing folding device comprises a wing hinge, an actuating device and a locking device, and realizes v-type, z-type and w-type folding.

3. A folding stowable variant aircraft according to claim 1, wherein: each wing section consists of a front edge, a wing box and a rear edge, and the front edge, the wing box and the rear edge are connected through an actuating mechanism and a locking mechanism to realize folding.

4. A folding stowable variant aircraft according to claim 1, wherein: the tail wing comprises two tail wing surfaces (12) and a root rotating shaft, and the tail wing surfaces (12) are unfolded into a state perpendicular to the rear fuselage (2) through the rotation of the root rotating shaft.

5. A folding stowable variant aircraft according to claim 1, wherein: the propeller comprises two foldable blades (13), and the folded propeller (13) is unfolded into a vertical rear machine body (2) state through centrifugal force generated by motor rotation; the foldable blade (13) has a function of folding forward or backward.

6. A folding stowable variant aircraft according to claim 1, wherein: the wing has a large aspect ratio.

7. A folding stowable variant aircraft according to claim 1, wherein: the cylinder body (14) is in a cylindrical shell split configuration, and the aircraft is restrained in the cylinder body (14) after being retracted, so that the aircraft is prevented from being damaged in the delivery process.

8. A folding stowable variant aircraft according to claim 1, wherein: the wing parts in the folded state are rotated to be perpendicular to the fuselage from a state parallel to the fuselage in the folded state around the root rotating shaft of the wing.

9. A folding stowable variant aircraft according to claim 3, characterized in that: the wing is rotated and unfolded, and meanwhile, the front edge, the wing box and the rear edge of the wing are also moved from a slotting folding state to a complete splicing state through an actuating mechanism and a locking mechanism.

10. A folding stowable variant aircraft according to claim 1, wherein: the front end part of the front machine body (1) is provided with a protruding part, the rear end part of the rear machine body (2) is provided with a shrinking part, and the protruding part is matched with the shrinking part.

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