CN203577324U - Remote control aircraft provided with folding undercarriage - Google Patents

Abstract

The utility model relates to a remote control aircraft provided with a folding undercarriage. According to the remote control aircraft provided with the folding undercarriage, the skid type undercarriage is mounted at the lower end of a main machine and comprises supports, sliding rods, tilting parts and stabilizing plates, the two sides of the lower end of a machine shell are respectively provided with two supports in a symmetrical and fixed mode, the supports on the two sides are both inclined from front to back, the lower ends of the supports on the two sides are respectively provided with a transverse sliding rod in a symmetrical and fixed mode, the tilting parts tilting upwards by the same radian are formed at the front ends of the sliding rods on the two sides respectively, the rear portions of the sliding rods on the two sides are respectively provided with a horizontally arranged stabilizing plate in a fixed mode, a rotary shaft structure is mounted on the upper portion of each support, and the rotary shaft structures are all connected to a circuit control device through lines. The remote control aircraft provided with the folding undercarriage is flexible and fast in use, stable in flight, convenient to control remotely, good in operation performance, sensitive in response, good in flight stability and landing stability, simple in structure, convenient to dismount, convenient to maintain, reliable in structure, long in service life, low in overall weight, and stable in landing.

Description

Telecontrolled aircraft with folding undercarriage

Technical field

The utility model belongs to toy field, especially a kind of telecontrolled aircraft with folding undercarriage.

Background technology

Telecontrolled aircraft can far distance controlled the aircraft of flight.Telecontrolled aircraft has entered in average family at present, wherein to play, takes direction as the leading factor; Also there is part fan to reequip it, to reach more entertainment way (as take photo by plane, load-carrying etc.).Remote controller sends signal, and the receiver on aircraft receives signal, and receiver is passed to steering wheel signal and electric energy, and steering wheel rotates, drivening rod, operating aircraft flight.

At present, the operating flying angle of common unmanned plane is smaller, and the wing of unmanned plane and empennage can both produce enough lift in this state, can guarantee the normal flight of unmanned plane.But when the unmanned plane angle of attack increases gradually, the empennage of unmanned plane will be absorbed in the low energy wake flow of wing, may cause empennage stall, even make unmanned plane enter tailspin and cause crashing, now, although motor is working properly, also cannot makes unmanned plane keep balance and rest on aerial.This is mainly to control because present telecontrolled aircraft structure mainly relies on circuit, in order to alleviate overall weight, simplify member as far as possible, motor places one's entire reliance upon while controlling state of flight, and flight stability is poor, especially during aircraft landing, often, because the landing place aircraft that causes lack of standardization is difficult to safe landing, cause aircraft damage, even damage.

Utility model content

The purpose of this utility model is to overcome the deficiencies in the prior art part, the telecontrolled aircraft that a kind of simple in structure, reliable, long service life, flight stability is provided, lands stably with folding undercarriage.

The utility model solves its technical problem and takes following technical scheme to realize:

A kind of telecontrolled aircraft with folding undercarriage, comprise casing, rotor device, drive unit, remote-receiver and circuit control device, described casing top middle portion is provided with rotor device, this rotor device is mounted on the drive unit in casing, remote-receiver and circuit control device are installed in casing, it is characterized in that: a mechanical universal gyroscope is installed in described casing, this universal gyroscope comprises shell, housing axle torquer, housing axle, housing, inside casing, inner axis, rotor, inner axis torquer, sensor and armature spindle, shell is the cylinder barrel shaped structure of sealing, the longitudinal two ends of this shell are all coaxially installed with a housing axle torquer, between the housing axle torquer at these longitudinal two ends, be coaxially installed with housing axle, this housing axle middle part is coaxially fixed with the housing of a rectangular box structure, the transverse ends of this housing is all coaxially installed with inside casing rotating shaft torquer, this transverse ends inside casing rotating shaft torquer between be coaxially installed with an inner axis, this inner axis middle part is coaxially fixed with the inside casing of a quadrilateral structure, this inside casing middle part is provided with a rotor by armature spindle, this armature spindle direction is mutually vertical with inner axis direction,

Described casing lower end is provided with skid landing gear, this skid landing gear comprises support, slide bar, perk and steadying plate, in both sides, casing lower end, equal symmetry is fixed with two supports, the support of these both sides is by front receding, the support lower end of these both sides is the symmetrical horizontal slide bar that is fixed with respectively, the slide bar front end of these both sides is all shaped with the perk that identical radian measure upwards curves, and the slide bar rear portion of both sides is all fixed with the steadying plate of a horizontal direction; Described support top is all provided with a pivot structure, and this pivot structure arrives circuit control device by connection.

And described support is elastic extension structure, buffer spring is all installed between support lower end and slide bar.

Advantage of the present utility model and good effect are:

It is flexible, quick that the utility model is used, and flight stability, is convenient to straighforward operation, and handling is quick on the draw well, flight stability and flooring stability are better, and simple in structure, easy accessibility, are convenient to safeguard, reliable in structure, long service life, overall weight is light, lands steadily.

Accompanying drawing explanation

Fig. 1 is structural representation of the present utility model;

Fig. 2 is the ski structure enlarged diagram in the utility model;

Fig. 3 is the universal gyroscope internal structure schematic diagram in the utility model.

The specific embodiment

Below in conjunction with accompanying drawing and by specific embodiment, the utility model is described in further detail, and following examples are descriptive, are not determinate, can not limit protection domain of the present utility model with this.

A kind of telecontrolled aircraft with folding undercarriage, comprise casing 1, rotor device 3, drive unit 2, remote-receiver and circuit control device, described casing top middle portion is provided with rotor device, this rotor device connecting drive device, is provided with remote-receiver and circuit control device (not shown) in casing.

Innovative point of the present utility model is:

In order to promote flight and landing stability and the flight attitude adjustment flexibility of telecontrolled aircraft, one mechanical universal gyroscope is installed in described casing, this universal gyroscope is connected to circuit control device by sensor, this universal gyroscope concrete structure as shown in Figure 2, comprise shell 102, housing axle torquer 101, housing axle 110, housing 103, inside casing 105, inner axis 109, rotor 104, inner axis torquer 106, sensor 107 and armature spindle 108, shell is the cylinder barrel shaped structure of sealing, the longitudinal two ends of this shell are all coaxially installed with a housing axle torquer, between the housing axle torquer at these longitudinal two ends, be coaxially installed with housing axle, this housing axle middle part is coaxially fixed with the housing of a rectangular box structure, the transverse ends of this housing is all coaxially installed with inside casing rotating shaft torquer, this transverse ends inside casing rotating shaft torquer between be coaxially installed with an inner axis, this inner axis middle part is coaxially fixed with the inside casing of a quadrilateral structure, this inside casing middle part is provided with a rotor by armature spindle, this armature spindle direction is mutually vertical with inner axis direction.Gyroscope arrangement of the present utility model is simple, and quality is light, and structure is arranged in the box body of sealing and can not impact interior of aircraft structure, compares with existing detection of electrons element, and susceptibility is better, and working stability is reliable.

As long as gyroscope time is given its tripping force in work, it is rotated, get final product work really long days, little for power requirement amount, alleviate the workload of aircraft load battery.By several different methods, read the indicated direction of axle, and automatically data-signal is passed to control system, gyroscopic instrument can provide orientation, level, position, speed accurately.Gyroscopic instrument not only can be used as indicating meter, and the more important thing is that it can be used as a sensing element in automatic control system, can be used as signal transducer, in landing process, adjusts more quickly, guarantees aircraft landing safety.

In order to promote the stationarity of landing of this telecontrolled aircraft, described in the present embodiment, main frame lower end is provided with skid landing gear, this skid landing gear comprises support 6, slide bar 5, perk 7 and steadying plate 4, in both sides, casing lower end, equal symmetry is fixed with two supports, the support of these both sides slows down the direct impulsive force of landing by the certain angle that front recedes, the support lower end of these both sides is the symmetrical horizontal slide bar that is fixed with respectively, the slide bar front end of these both sides is all shaped with the perk that identical radian measure upwards curves, the slide bar rear portion of both sides is all fixed with the steadying plate of a horizontal direction, increase and to land planing stability, prevent that fuselage overturning from causing damage.

In order to reduce resistance awing, save parking space, described skid landing gear is folding structure, and support top is all provided with a pivot structure 8, when folding, undercarriage integral body stacks casing lower end to back upper place, and this pivot structure arrives circuit control device by connection.

In order to slow down impulsive force, prevent damage, described support is elastic extension structure, as shown in Figure 3, buffer spring 9 is all installed between support lower end and slide bar, when undercarriage impacts ground, rack elasticity is flexible, keeps the stable rigid collision damage fuselage that prevents of fuselage.

Although disclose for the purpose of illustration embodiment of the present utility model and accompanying drawing, but it will be appreciated by those skilled in the art that: within not departing from the spirit and scope of the utility model and claims, various replacements, variation and modification are all possible, therefore, scope of the present utility model is not limited to embodiment and the disclosed content of accompanying drawing.

Claims (2)

1. the telecontrolled aircraft with folding undercarriage, comprise casing, rotor device, drive unit, remote-receiver and circuit control device, described casing top middle portion is provided with rotor device, this rotor device is mounted on the drive unit in casing, remote-receiver and circuit control device are installed in casing, it is characterized in that: a mechanical universal gyroscope is installed in described casing, this universal gyroscope comprises shell, housing axle torquer, housing axle, housing, inside casing, inner axis, rotor, inner axis torquer, sensor and armature spindle, shell is the cylinder barrel shaped structure of sealing, the longitudinal two ends of this shell are all coaxially installed with a housing axle torquer, between the housing axle torquer at these longitudinal two ends, be coaxially installed with housing axle, this housing axle middle part is coaxially fixed with the housing of a rectangular box structure, the transverse ends of this housing is all coaxially installed with inside casing rotating shaft torquer, this transverse ends inside casing rotating shaft torquer between be coaxially installed with an inner axis, this inner axis middle part is coaxially fixed with the inside casing of a quadrilateral structure, this inside casing middle part is provided with a rotor by armature spindle, this armature spindle direction is mutually vertical with inner axis direction,

Described casing lower end is provided with skid landing gear, this skid landing gear comprises support, slide bar, perk and steadying plate, in both sides, casing lower end, equal symmetry is fixed with two supports, the support of these both sides is by front receding, the support lower end of these both sides is the symmetrical horizontal slide bar that is fixed with respectively, the slide bar front end of these both sides is all shaped with the perk that identical radian measure upwards curves, and the slide bar rear portion of both sides is all fixed with the steadying plate of a horizontal direction; Described support top is all provided with a pivot structure, and this pivot structure arrives circuit control device by connection.

2. the telecontrolled aircraft with folding undercarriage according to claim 1, is characterized in that: described support is elastic extension structure, and buffer spring is all installed between support lower end and slide bar.

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