CN202414160U

CN202414160U - Vertical take-off and landing morphing aircraft

Info

Publication number: CN202414160U
Application number: CN2011204520539U
Authority: CN
Inventors: 王劲; 周军; 孙兆虎; 宋艳平; 房元鹏
Original assignee: AVIC Chengdu Aircraft Design and Research Institute
Current assignee: AVIC Chengdu Aircraft Design and Research Institute
Priority date: 2011-11-15
Filing date: 2011-11-15
Publication date: 2012-09-05
Anticipated expiration: 2021-11-15

Abstract

The utility model belongs to the field of aircraft design, which relates to a small vertical take-off and landing morphing aircraft. The aircraft comprises a middle wing section, a main wing section, a folding wing section, a folding mechanism, vertical fins, a power part and a reconnaissance equipment compartment; the vertical fins are symmetrical to the upper and the lower surfaces of the aircraft and symmetrically installed between the middle wing section and the main wing section; the rear end of each vertical fin extends out of the tail of the middle wing section; the main wing section is connected with the folding wing section through the folding mechanism; the folding mechanism comprises a folding rotating shaft parallel with the body axis of the aircraft; the folding mechanism is arranged in the main wing section; and the folding wing section performs 180-degree uniform folding around the folding rotating shaft. The aircraft adopts a new morphing mode, can simultaneously change the aspect ratio and the wing profile, and has a wider deformation range, a better flight performance, a simple morphing mechanism and higher engineering realizability.

Description

VTOL variant aircraft

Technical field

The utility model belongs to the Flight Vehicle Design field, relates to a kind of small-sized VTOL variant aircraft.

Background technology

The variant aircraft can change self aerodynamic configuration according to the needs of mission requirements or flight environment of vehicle, makes current profile adapt to new flying condition, thereby makes aircraft under various state of flight, and airworthiness can both reach higher level.

The variant aircraft can be according to the various tasks demand; Take into account high/low speed airworthiness, improve the takeoff and landing performance of aircraft and grasp steady characteristic, improve the manoevreability of aircraft; Also can improve simultaneously flying power, increase airborne period, weather-proof war fighting requirement when navigating to adapt to length.

At present, existing variant aircraft mainly reaches the variant purpose to change wing shapes or to change the wing bending among a small circle, and such variant aircraft can only carry out discontinuous distortion among a small circle; So; The lifting of its performance is not very remarkable, and based on full intellectual material and the technological variant aircraft of adaptive structure, though can realize the variation that aerodynamic configuration is smooth, continuous; Satisfy high low speed airworthiness, manoevreability and the duration performance of aircraft better; Improve road-holding property, enlarge the task scope of aircraft, it is very superior to improve its combat duty adaptive capacity performance; But the restriction that it receives material technology, control technology and mechanical technology level also needs long time just can obtain critical progress and breakthrough.

Summary of the invention

The purpose of the utility model is to propose a kind of simple in structure, manoevreability and the good VTOL variant aircraft of duration performance.The technical solution of the utility model is; Wing panel, main wing section, folding wing panel, fold mechanism, vertical fin, power pack section and recce pack in the middle of aircraft comprises; The vertical fin of aircraft is symmetrical in the upper surface and the lower surface of aircraft; Be symmetrically installed with between the middle wing panel and main wing section of aircraft, the afterbody of the middle wing panel of aircraft is stretched out in the rear end of vertical fin; The main wing section is connected by fold mechanism with folding wing panel, and fold mechanism comprises a folding rotating shaft parallel with the aircraft axis, and fold mechanism places in the main wing section, and folding wing panel is carried out 180 ° at the uniform velocity folding around folding rotating shaft.

Described folding wing panel is carried out at the uniform velocity folding around folding rotating shaft, folding wing panel and main wing section are fitted, and form a symmetrical airfoil.

Described vertical fin is a supporter.

Advantage that the utlity model has and beneficial effect; The utility model has used a kind of brand new variant mode, can change aspect ratio and aerofoil profile simultaneously, and its deformation range is wideer and airworthiness is more superior; And this variant mechanism is comparatively simple, and the engineering realizability is stronger.Simultaneously, multiple function that the utility model is simultaneously also integrated can be carried out multiple different task.The utility model possesses following function simultaneously, and (1) vertical/the STOL function:

When individual soldier or team do wartime, under the narrow and small battlefield surroundings in landing spatial domain, this unmanned plane place at any time can be carried out investigation tasks, and convenient the recovery.

(2) hover and stare the scouting function: because this unmanned plane can aloft be stablized and hover; And its investigation equipment has the visual range of pitching ± 90 °, lift-over ± 180 °; So this unmanned plane all has the good scouting visual field under any offline mode; Can confirm that target continues to observe to certain, be well suited for accomplishing the reconnaissance mission of low latitude and street fighting situation.

(3) function is scouted in static standby: because this aircraft can VTOL; When executing the task in the sky, city especially; Drop to certain higher buildings thing top after can changing the vertical landing pattern over to, close and carry out long-time static standby behind the power and scout, take off vertically back and returning of the back actuating motor of finishing the work; Because this scouting pattern does not need consumption of power, can improve the time of carrying out reconnaissance mission greatly.

(4) high maneuverability can: can the quick approach target after taking off, after finishing the work, withdraw the battlefield rapidly, and can pass through the rapid change of self state of flight, hide attack from ground-surface light ammunition.

(5) the aerial wing function launching/pack up, pattern when aircraft can be long boat by the maneuvering flight mode converting rapidly: behind the unmanned plane quick approach target sky, pattern when converting long boat into can be monitored target for a long time.

Description of drawings

Fig. 1 is the utility model structural representation;

Fig. 2 is the folding wing panel deployed configuration scheme drawing of the utility model;

Fig. 3 is the birds-eye view of Fig. 2;

Fig. 4 is the folding wing panel of the utility model structural representation when folding;

Fig. 5 is the birds-eye view of Fig. 4;

Fig. 6 is the side-looking of Fig. 4.

The specific embodiment

Below in conjunction with accompanying drawing the utility model is elaborated.Wing panel 1, main wing section 2, folding wing panel 3, fold mechanism 4, vertical fin 5, power pack section 6 and recce pack 7 in the middle of aircraft comprises; Vertical fin 5 is symmetrical in the upper surface and the lower surface of aircraft; Be symmetrically installed with between the middle wing panel 1 and main wing section 2 of aircraft, the afterbody of the middle wing panel 1 of aircraft is stretched out in the rear end of vertical fin 5; Main wing section 2 is connected by fold mechanism 4 with folding wing panel 3, and fold mechanism 4 comprises a folding rotating shaft 8 parallel with the aircraft axis, and fold mechanism 4 places in the main wing section 2, and folding wing panel 3 is carried out 180 ° at the uniform velocity folding around folding rotating shaft 8.

(1) among Fig. 1, VTOL variant aircraft is made up of middle wing panel 1, main wing section 2, folding wing panel 3, fold mechanism 4, vertical fin 5, power pack section 6 and recce pack 7.

(2) among Fig. 2,3, the folded part of VTOL variant aircraft is made up of main wing section 2 and folding wing panel 3, arranges the folding rotating shaft 8 parallel with axis between two wing panels; Through at main wing section 2 internal placement actuator and fold mechanism 4; Make folding wing panel 3 to carry out 180 ° at the uniform velocity folding, after folding wing panel 3 is folding fully and 2 applyings of main wing section around folding rotating shaft 8; Form a symmetrical airfoil, as shown in Figure 4:

Because folding wing panel 3 overlaps with main wing section 2, the wing exhibition is long to be reduced, and chord length is constant, so blade area reduces, aspect ratio diminishes, thereby reaches the purpose of change of flight device aerodynamic configuration.

(3) vertical fin 5 of VTOL variant aircraft is taken into account the alighting gear function simultaneously, and disposes suitable power, and the thrust-weight ratio that makes aircraft is greater than 1, thereby this aircraft has VTOL and hover capabilities, and is as shown in Figure 1.

Claims

1. VTOL variant aircraft; Wing panel (1), main wing section (2), folding wing panel (3), fold mechanism (4), vertical fin (5), power pack section (6) and recce pack (7) in the middle of comprising; It is characterized in that; Vertical fin (5) is symmetrical in the upper surface and the lower surface of aircraft, is symmetrically installed with between the middle wing panel (1) and main wing section (2) of aircraft, and the afterbody of the middle wing panel of aircraft (1) is stretched out in the rear end of vertical fin (5); Main wing section (2) is connected by fold mechanism (4) with folding wing panel (3); Fold mechanism (4) comprises a folding rotating shaft (8) parallel with the aircraft axis; Fold mechanism (4) places in the main wing section (2), and folding wing panel (3) is carried out 180 ° at the uniform velocity folding around folding rotating shaft (8).

2. a kind of VTOL variant aircraft according to claim 1 is characterized in that, described folding wing panel (3) is carried out at the uniform velocity folding around folding rotating shaft (8), and folding wing panel (3) is fitted with main wing section (2), forms a symmetrical airfoil.

3. a kind of VTOL variant aircraft according to claim 1 is characterized in that described vertical fin (5) is a supporter.