Retractable tail boom undercarriage of tail sitter type vertical takeoff and landing aircraft

Abstract

The invention discloses a retractable tail boom undercarriage of a tail sitter type vertical takeoff and landing aircraft. The retractable tail boom undercarriage consists of the tail sitter type vertical takeoff and landing aircraft, main landing gears, a tail boom, supporting rods, tail boom driving mechanisms and supporting rod driving mechanisms, wherein the main landing gears are symmetrically arranged below the tail sitter type vertical takeoff and landing aircraft and serve as main supporting components of the aircraft parking on the ground. The tail boom and the supporting rods are respectively mounted on the upper side and the lower side of wings of the aircraft; the tail boom is provided with tail boom rods, vertical fins, a horizontal tail and horizontal tail driving mechanisms;the tail boom driving mechanisms and the supporting rod driving mechanisms are symmetrically arranged on two sides of an aircraft fuselage and are used for driving the tail boom and the supporting rods to be opened or closed; the retractable tail boom undercarriage realizes a supporting effect when the aircraft parks on the ground and realizes the effects of manipulating and balancing the aircraft when the aircraft is in a horizontal flying state. The retractable tail boom undercarriage of the tail sitter type vertical takeoff and landing aircraft has the characteristics of compact structure,light weight and multiple functions.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a retractable tail brace landing gear of a tail-sitting vertical take-off and landing aircraft. Background technique [0002] The tail-sitting vertical take-off and landing aircraft is supported on the ground by the landing gear installed at the tail. In order to maintain the balance of the aircraft on the ground and not damage the aircraft, it is necessary to have a large span of the support points of the landing gear, so that the aircraft is subject to external disturbances or small When the angle is tilted, the aircraft is still stable. These support structures can protect and support the aircraft when the aircraft takes off and land, but they are heavy and will increase the flight resistance when the aircraft is cruising, which will affect the cruising performance of the aircraft. [0003] At present, tail-sitting vertical take-off and landing aircraft generally adopt a lay...

AI Technical Summary

Problems solved by technology

[0002] The tail-sitting vertical take-off and landing aircraft is supported on the ground by the landing gear installed at the tail. In order to maintain the balance of the aircraft on the ground and not damage the aircraft, it is necessary to have a large span of the support points of the landing gear, so that the aircraft is subject to external disturbances or small When the angle is tilted, the aircraft is still stable. These support structures can protect and support the aircraft when the aircraft takes off and land, but they are heavy and will increase the flight resistance when the aircraft is cruising, which will affect the cruising performance of the aircraft.

[0003] At present, tail-sitting vertical take-off and landing aircraft generally adopt a layout without horizontal tail, mainly to reduce the distance between the center of gravity of the aircraft and the ground, and improve the stability of the aircraft supported on the ground and during take-off and landing. Longitudinal trim is more difficult

The longitudinal channel of the aircraft is usually a static and stable layout, which requires the horizontal tail to generate negative lift, so that the aircraft is trimmed at the desired angle of attack. The horizontal tail of conventional aircraft is far from the center of gravity of the aircraft, and the horizontal tail trim arm is long, requiring only a small load. Lift can be trimmed, so the additional drag is limited

However, for a tail-sitting VTOL aircraft without a horizontal tail, in the horizontal flight stage, the elevon usually needs to generate negative lift to keep the aircraft in level flight. At this time, the elevon is close to the center of gravity and the moment arm is short, which will Larger additional resistance, the lift-drag ratio of the aircraft's horizontal flight is low, making the cruise efficiency of the aircraft lower

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