阅读说明：本技术 推力转向式飞机 (Thrust steering aircraft ) 是由 E·V·齐门斯卡亚 于 2018-12-17 设计创作，主要内容包括：本发明涉及航空领域,尤其涉及垂直起降飞机结构。推力转向式飞机包括机身、一对机翼：前翼和后翼、包括发动机和螺旋桨的发动机单元、鳍部、起落架、为旋转配置的吊架。两个起重发动机单元位于机身两侧的吊架上,该吊架的具有俯仰角/倾斜度两个自由度,用于固定位置并向前或向后缩回机身槽中。推进系统安装在具有一个俯仰角自由度的吊架上,并且构造成固定位置或牢固安装,且定位在机身的前部或后部,以及鳍部的前缘或后缘。推力转向式飞机的可靠性得到提高,使用寿命延长,增加了飞行距离,并降低了成本。(The invention relates to the field of aviation, in particular to a vertical take-off and landing aircraft structure. The thrust steering aircraft comprises a fuselage and a pair of wings: front and rear wings, an engine unit comprising an engine and a propeller, fins, landing gear, a pylon configured for rotation. Two crane motor units are located on the pylons on either side of the fuselage, which pylons have two degrees of freedom in pitch/inclination for securing the position and retracting forward or backward into the fuselage slots. The propulsion system is mounted on a pylon with one degree of freedom of pitch angle and is configured for fixed or firm mounting and positioning at the front or rear of the fuselage and the leading or trailing edge of the fin. The thrust steering aircraft has improved reliability, prolonged service life, increased flight distance, and reduced cost.)

1. A thrust steered aircraft comprising: fuselage, a pair of wing: front and rear wings, a fin, two hoist engine units comprising an engine with a propeller located above a pylon having two pitch/tilt degrees of freedom on the side of the fuselage, arranged in a fixed position and retracted into the fuselage cell in horizontal flight, the propulsion system comprising an engine located on the pylon, characterised in that the propulsion system pylon has only one pitch attitude degree of freedom and is arranged in a fixed position, or no degree of freedom.

2. The thrust steer aircraft of claim 1, wherein said lift engine is designed as an electric, conventional, or gas turbine engine.

3. The thrust steer aircraft of claim 1, wherein the propeller of said lift engine unit is collapsible.

4. The thrust steer aircraft of claim 1, wherein said lift motor unit is retractable forward or aft into a fuselage slot.

5. The thrust steer aircraft of claim 1, wherein said propulsion system engine is designed as an electric or conventional engine and the fixed or controllable propeller is foldable or non-foldable.

6. The thrust steer aircraft of claim 1, wherein said propulsion system engine comprises or lacks jet engines and thrust vector control surfaces.

7. The thrust steer aircraft of claim 1, wherein said propulsion system pylon is located in a forward or aft portion of said fuselage and is also located on a leading or trailing edge of said fin.

8. The thrust steerable aircraft of claim 1, further comprising a landing gear.

9. The thrust steerable aircraft of claim 1, further comprising a parachute.

Technical Field

The invention relates to the field of aviation, in particular to a vertical take-off and landing aircraft structure. The invention can be used in all fields relating to the traditional use of airplanes, helicopters, thrust steered airplanes, unmanned airplanes.

Background

A thrust steer type aircraft (patent RU No. 246209c1. ipc B64C37/00-20.07.2012, publication No. 20) is known, which includes a fuselage, wings, an engine, a tail unit, and landing gears. A pylon configured for rotation is located on the wing. Two front engines are mounted on the hanger. The rear engine is mounted on the fin pylon. Landing gear legs are coupled to the wing pylons and the fin portions (fin), respectively. The aircraft is ensured to be balanced in all flight modes.

The disadvantageous features of this solution are low lifting capacity, short flight distance and short flight time due to the low efficiency of the engine unit, since the engine unit is lifted and propelled simultaneously and the engine is overloaded in horizontal flight and thus forced to operate at low efficiency.

The closest claimed solution is a thrust steered aircraft (RU No.2635431C1, IPCB64C37/00-13.11.2017, publication No. 32) comprising a fuselage, a pair of wings (front and rear), an engine unit including an engine and a propeller, a landing gear, a pylon in a swivel arrangement, two lift engine units on the pylon, the pylon having two respective pitch/tilt degrees of freedom for securing the position in horizontal flight and retracting forward or backward into the fuselage slot. The propulsion system is mounted on the pylon in two pitch angles/degrees of freedom and is configured to be fixed to the rear of the fuselage. This patent is taken as a prototype.

The disadvantages of such an aircraft are as follows:

1. the propulsion system hanger has heavy weight and high resistance.

2. When using an internal combustion engine in the propulsion system, the technical complexity of the control system increases. This is based on the fact that: internal combustion engines are much more speed inert than electric engines and therefore cannot be used in a control loop without a controllable pitch propeller in conventional engines and gas turbine engines or without a controllable nozzle using jet engines.

Disclosure of Invention

The object of the claimed invention is to create a transport thrust steer aircraft of simple design that is balanced in all flight modes and capable of horizontal flight, vertical take-off and landing and hovering in place. In terms of practicality, the thrust steered aircraft can take off and land within minimum dimensional dimensions and reduced transit times due to the ability to bring the payload as close as possible to the customer.

The technical result is as follows: the structure reliability is improved, the hoisting capacity, the flight distance and the time are increased, and the cost of the thrust steering type machine is reduced.

The technical result is obtained by the fact that: thrust steered aircraft comprising a fuselage, a pair of wings (front and rear), two lift engine units comprising an electric engine or a conventional engine or a gas turbine engine, and fixed or controllable propellers (folded or unfolded) on a pylon with two degrees of pitch/tilt freedom, the pylon being located at the side of the fuselage and being usable in a fixed position, retractable forwards or backwards into a fuselage slot, a propulsion system comprising an electric engine or a conventional engine, and fixed or controllable, selectively foldable pitch propellers, or a jet engine and optionally a thrust vector control surface, the propulsion system being located on the pylon and being configured to be located at the front or rear of the fuselage and at the leading or trailing edges of fins, landing gear, parachute optionally configured, and fins, characterized in that the propulsion system pylon has only one degree of pitch/tilt freedom, and is configured to be fixed in position, or has no degree of freedom.

The advantages ensured by the aforementioned set of characteristics are a reduction in technical complexity, a reduction in costs and an increase in reliability, and also a reduction in the unloaded fuselage weight of the thrust steer aircraft and an increase in the flight distance and time. It ensures that the above advantages are achieved by reducing the pylon freedom of the propulsion system and by eliminating the propulsion system entirely or partially from the thrust steer aircraft control loop.

Drawings

The main content of the invention is supported by the following figures:

FIG. 1-an overall view of a thrust steerable aircraft in a takeoff and landing mode. The propulsion system pylon has one degree of freedom;

FIG. 2-thrust steer aircraft acceleration;

fig. 3 is a general view of a thrust steered aircraft in horizontal flight. The hoisting motor unit retracts into the fuselage slot;

fig. 4-an overall view of a thrust steered aircraft in takeoff and landing modes. The propulsion system is stationary. Wherein:

1-a fuselage;

2-front wing;

3-tail fin;

4-a fin portion;

5-a hoist engine unit;

6-a propulsion system;

7. 8-differential aerodynamic control means;

9-hoisting engine pylon;

10-propulsion system pylon;

11-fuselage slots for retrieving the hoisting engines.

Detailed Description

The invention comprises a fuselage 1 designed for arranging payloads, elements of control systems and other systems; front wing 2 and rear wing 3; a fin portion 4; lifting engine units 5 for starting the engines and propellers, which are located on the rotating cradles 9 on both sides of the fuselage, to generate lift in takeoff/landing mode; a propulsion system 6, including an engine and propellers or without propellers, on a pylon 10, the pylon 10 being arranged at the front or rear of the fuselage and at the leading or trailing edge of the fin; differential aerodynamic control devices 7 and 8 for aircraft horizontal flight control; a fuselage slot 11 for retrieving the hoist engine unit.

The present invention has several features:

1. the propulsion system pylon has one degree of freedom in pitch, or no degree of freedom.

2. If the propulsion system pylon has one degree of freedom, the thrust steered aircraft is controlled longitudinally by the propulsion system speed, the collective pitch (if a controllable propeller is mounted) and by rotation of the pitch angle of the propulsion system pylon and by means of the crane engine unit and its pylon.

3. When the propulsion system pylon is fixed and the propulsion system includes jet engines and thrust vectoring control surfaces, the thrust steer aircraft is controlled longitudinally by engine thrust, thrust vectoring control surfaces, and the lift engine unit and its pylon.

4. In the takeoff and landing mode, the thrust steering aircraft is controlled by the pitch angle differential rotation of the crane engine unit.

5. If the propulsion system is stationary and there is no means for rotating the propulsion system in a vertical plane, the thrust steered aircraft is controlled longitudinally by pitch/tilt angle rotation of the crane engine unit pylon and by hoist engine speed (by controlling the pitch of the propellers, where they are controllable).

The device operates as follows: there are three total modes of flight of the aircraft: take-off landing mode, acceleration mode and horizontal flight.

If the propulsion system pylon has one degree of freedom, then in the takeoff landing mode (FIG. 1), all three engine units will be operated and placed in the "on" operating position. Control is achieved by rotation of the motor unit relative to the rotation of the a and B axes (pitch attitude) and rotation of the propulsion system relative to the rotation of the C axis (pitch attitude). The deflection is performed by a servo driver. Furthermore, the thrust steer type aircraft is controlled by varying the engine speed.

After takeoff, all engine units are rotated forward at an angle to generate horizontal thrust (fig. 2). Thus, the thrust steered aircraft accelerates to a minimum horizontal flight speed. Thereafter, the hoist engine unit is stopped and retracted into the fuselage slots by rotating the nacelle about the a-axis (pitch angle). In horizontal flight (fig. 3), lift is generated by the wings, thrust is generated by the propulsion system, and control is performed by differential control (which may be mounted on the front and/or rear wings). If the propulsion system fails, it can be landed by a crane motor unit or by a "taxi" method (via differential control) or parachute (if present).

If the propulsion system is installed securely and has no thrust vector control surfaces, then in the takeoff and landing mode, the thrust steered aircraft is controlled solely by the lift engine unit, with the propulsion system in an off or idle state. The thrust steered aircraft is accelerated to a minimum horizontal airspeed by rotating the hoist engine forward through an angle to produce horizontal thrust while the propulsion system is activated to produce thrust. When the lowest horizontal flying speed is reached, the lift motor unit will retract into the fuselage. The manner in which horizontal flight and landing are performed is similar to the previous configuration.

If the propulsion system is firmly mounted and comprises jet engines and thrust vector control surfaces, the thrust steered aircraft is controlled longitudinally by these control surfaces as well as the crane engine unit and its pylon.

Compared to prototypes, the claimed solution has several advantages, namely:

1. when the propulsion system pylon has one degree of freedom, the weight of the unloaded thrust steer aircraft is reduced by 5% due to the lack of a roll mechanism. Furthermore, the structure is technically simplified.

2. With the propulsion system fixed, the unloaded thrust steer aircraft has a weight reduction of 10%, technically simplified construction and improved reliability, and in addition it is possible to use an internal combustion engine without a controllable pitch propeller, which also results in weight reduction, simplification of construction and control system and improved reliability of the aircraft.

3. The use of jet engines in propulsion systems allows a thrust steered aircraft to reach supersonic speeds.

4. If the propulsion system is firmly mounted and comprises jet engines and thrust vector control surfaces, the power requirements of the lift engine units will be reduced and therefore their weight and size will be reduced, as will the pylon weight of the propulsion system, simplifying its technical complexity due to the lack of two degrees of freedom. As a result, the flight distance and time of the thrust steer aircraft are increased, simplifying its technical complexity and increasing reliability.