Method of landing rotorcraft without alighting run with autorotating rotor and wing. RU patent 2506203.
 Gyroplane with vertical take-off and vertical landing / 2463213Invention relates to aircraft, in particular to vertical take-off and landing aircraft. Gyroplane includes fuselage (1) with flight deck with folding pillar (2) installed on it, rotor head (3) with adjustable torsion bushing (16) and pusher screw (5) with adjustable pitch. In the rotor head (3) for even load distribution on torsion bushing (16) during preliminary spinup of rotor (4), torsion is made of flat composite plates without curve. Surface of tilting hinge (15) mounting of torsion bushing (16) is turned for angle not exceeding 40 degrees to longitudinal axis of bushing (16) torsion of rotor (4). Rotor (3) head is attached to pillar via frame hinge (9) with shifted forward trunnion (10). Pushing screw (5) has adjustable torsion bushing gathered of composite plates. All connections of rotor head tilt control rods and hinge joint of rotor spin-up shafts are positioned on axis of stand rotation. |
 Gyroplane / 2376200Gyroplane comprises aircraft airframe, rotor arranged on airframe with its blade rigidly fixed with rotor hub and aircraft internal combustion engine. Gyroplane airframe accommodates a pair of high-speed rotors comprising set of blades fitted at sweepback angle «» with respect to blade section peripheral speed vector «», where «» is the angle between blade front edge and plane perpendicular to vector «». Ends of adjacent swept-back blades are linked up and furnished with jet nozzles. Gyroplane additionally incorporates compressor coupled with aircraft internal combustion engine. |
 N dyadchenko's autugyro and windmill rotor / 2374135Invention relates to aircraft engineering, particularly to rotors. Proposed rotor comprises disk with blades. Proposed rotor represents a disk, which can be either bladed in sector sections of the disk or flexible with flexibility increasing from rotational axis to periphery, the disk oscillating and being attached unorthogonally to vertical or horizontal shaft. |
 Gyroplane / 2360837Gyroplane consists of cabin (1), chassis (2), empennage (3), lifting rotor, element of lifting rotor vanes (7) total pitch (6) control, power unit, mechanical transmission, including shaft and controlled friction coupling (11), which connects shaft to engine via angular gear (12). Transmission is equipped with controlled gear coupling (13), which connects shaft (10) to gear wheel (5) of lifting rotor bush (4) and system of quick disconnection of friction coupling whenever starting rotations of lifting rotors are obtained. Control of gear coupling is equipped with blocking device that excludes engagement of gear coupling at angles of total pitch of vanes that are different from minimum. |
 Gyroplane take-off method / 2327603Gyroplane take-off method include a maximum driving up the lift rotor by the running power plant with the minimum angle of total pitch to rpm exceeding the flight magnitude, cutting of the lift rotor, increasing the thrust to the maximum and take-off run on the surface. Here, the lift rotor is kept neutral or at a negative angle to the flow, the total pitch of the rotor blades has a minimum magnitude. Unsticking is effected on reaching the required speed by increasing the total pitch the lift rotor to the flight magnitude or to that exceeding the above by a safe difference. |
 Rotor head with torsion bar bush and fairing for autogyro at jump takeoff and vertical landing / 2313473Body of rotor head boss is secured to pylon through frame joint and bearing through which hollow shaft passes. Rod passing through hollow shaft is connected with rocker arm shaft through bearing race. Gear wheel is fitted on hollow shaft rigidly or through overrunning clutch depending on rotor spinning-up drive. Gear wheel may be rigidly mounted on hollow shaft; gear of rotor spinning-up drive is mounted via Bendix drive or on hinged joint. Gear wheel may be mounted on shaft via overrunning clutch; gear of rotor spinning-up drive is thrown into constant engagement with gear wheel. Rocker arm shaft has slot for performing translational motion and locking with pin. Rotor bush secured on hollow shaft by means of pin consists of swivel joint and torsion bar stacked from fiberglass laminates. Fairing mounted on rotor head plate performs function of force compensator. |
 Flying vehicle with electric drive / 2266236Proposed flying vehicle includes engine with power transmission, air propellers and wings. Used as primary engine is single-cylinder two-stroke double-acting internal combustion engine with two delivery cylinders located coaxially relative to working cylinder. Working and delivery cylinders are provided with magnetic pistons mounted on common rod articulated with mechanism converting rectilinear motion of rod into reciprocating motion. For converting mechanical energy into electrical energy, use is made of two-section field windings mounted on external surfaces of working and delivery cylinders and engageable with magnetic pistons. Field winding of working cylinder is electrically connected with primary winding of induction ignition coil. Field windings of delivery cylinders are electrically connected with stator windings of electric motors located on stator walls and rotor windings built in circumferential surfaces of propeller bands. |
 Autogyro rotor head / 2263047Proposed head has rotor hub unit connected with swivel joint of hub and aerodynamic surface connected with hub axle. This surface is so positioned that rated point of application of resultant aerodynamic force is shifted towards tail section of autogyro from axis of longitudinal swinging of hub. Aerodynamic surface is mounted on member rigidly connected with hub axle. Aerodynamic surface may be provided with device for change of its angle, may be located on either side from longitudinal plane of symmetry and may be symmetrical relative to this plane of symmetry. |
| Autogyro rotor head / 2263047 Proposed head has rotor hub unit connected with swivel joint of hub and aerodynamic surface connected with hub axle. This surface is so positioned that rated point of application of resultant aerodynamic force is shifted towards tail section of autogyro from axis of longitudinal swinging of hub. Aerodynamic surface is mounted on member rigidly connected with hub axle. Aerodynamic surface may be provided with device for change of its angle, may be located on either side from longitudinal plane of symmetry and may be symmetrical relative to this plane of symmetry. |
| Flying vehicle with electric drive / 2266236 Proposed flying vehicle includes engine with power transmission, air propellers and wings. Used as primary engine is single-cylinder two-stroke double-acting internal combustion engine with two delivery cylinders located coaxially relative to working cylinder. Working and delivery cylinders are provided with magnetic pistons mounted on common rod articulated with mechanism converting rectilinear motion of rod into reciprocating motion. For converting mechanical energy into electrical energy, use is made of two-section field windings mounted on external surfaces of working and delivery cylinders and engageable with magnetic pistons. Field winding of working cylinder is electrically connected with primary winding of induction ignition coil. Field windings of delivery cylinders are electrically connected with stator windings of electric motors located on stator walls and rotor windings built in circumferential surfaces of propeller bands. |
| Rotor head with torsion bar bush and fairing for autogyro at jump takeoff and vertical landing / 2313473 Body of rotor head boss is secured to pylon through frame joint and bearing through which hollow shaft passes. Rod passing through hollow shaft is connected with rocker arm shaft through bearing race. Gear wheel is fitted on hollow shaft rigidly or through overrunning clutch depending on rotor spinning-up drive. Gear wheel may be rigidly mounted on hollow shaft; gear of rotor spinning-up drive is mounted via Bendix drive or on hinged joint. Gear wheel may be mounted on shaft via overrunning clutch; gear of rotor spinning-up drive is thrown into constant engagement with gear wheel. Rocker arm shaft has slot for performing translational motion and locking with pin. Rotor bush secured on hollow shaft by means of pin consists of swivel joint and torsion bar stacked from fiberglass laminates. Fairing mounted on rotor head plate performs function of force compensator. |
| Gyroplane take-off method / 2327603 Gyroplane take-off method include a maximum driving up the lift rotor by the running power plant with the minimum angle of total pitch to rpm exceeding the flight magnitude, cutting of the lift rotor, increasing the thrust to the maximum and take-off run on the surface. Here, the lift rotor is kept neutral or at a negative angle to the flow, the total pitch of the rotor blades has a minimum magnitude. Unsticking is effected on reaching the required speed by increasing the total pitch the lift rotor to the flight magnitude or to that exceeding the above by a safe difference. |
| Gyroplane / 2360837 Gyroplane consists of cabin (1), chassis (2), empennage (3), lifting rotor, element of lifting rotor vanes (7) total pitch (6) control, power unit, mechanical transmission, including shaft and controlled friction coupling (11), which connects shaft to engine via angular gear (12). Transmission is equipped with controlled gear coupling (13), which connects shaft (10) to gear wheel (5) of lifting rotor bush (4) and system of quick disconnection of friction coupling whenever starting rotations of lifting rotors are obtained. Control of gear coupling is equipped with blocking device that excludes engagement of gear coupling at angles of total pitch of vanes that are different from minimum. |
| N dyadchenko's autugyro and windmill rotor / 2374135 Invention relates to aircraft engineering, particularly to rotors. Proposed rotor comprises disk with blades. Proposed rotor represents a disk, which can be either bladed in sector sections of the disk or flexible with flexibility increasing from rotational axis to periphery, the disk oscillating and being attached unorthogonally to vertical or horizontal shaft. |
| Gyroplane / 2376200 Gyroplane comprises aircraft airframe, rotor arranged on airframe with its blade rigidly fixed with rotor hub and aircraft internal combustion engine. Gyroplane airframe accommodates a pair of high-speed rotors comprising set of blades fitted at sweepback angle «» with respect to blade section peripheral speed vector «», where «» is the angle between blade front edge and plane perpendicular to vector «». Ends of adjacent swept-back blades are linked up and furnished with jet nozzles. Gyroplane additionally incorporates compressor coupled with aircraft internal combustion engine. |
| Gyroplane with vertical take-off and vertical landing / 2463213 Invention relates to aircraft, in particular to vertical take-off and landing aircraft. Gyroplane includes fuselage (1) with flight deck with folding pillar (2) installed on it, rotor head (3) with adjustable torsion bushing (16) and pusher screw (5) with adjustable pitch. In the rotor head (3) for even load distribution on torsion bushing (16) during preliminary spinup of rotor (4), torsion is made of flat composite plates without curve. Surface of tilting hinge (15) mounting of torsion bushing (16) is turned for angle not exceeding 40 degrees to longitudinal axis of bushing (16) torsion of rotor (4). Rotor (3) head is attached to pillar via frame hinge (9) with shifted forward trunnion (10). Pushing screw (5) has adjustable torsion bushing gathered of composite plates. All connections of rotor head tilt control rods and hinge joint of rotor spin-up shafts are positioned on axis of stand rotation. |
| Method of landing rotorcraft without alighting run with autorotating rotor and wing / 2506203 Invention relates to aircraft engineering, particularly, to landing of rotorcraft. Proposed method consists in that, first, preset speed is selected at glide path slope. Then, total pitch of the rotor is selected. Then, reverse is actuated of engine reversing devices are activated depending upon engine type at preset altitude above landing ground to brake the rotorcraft and to reduce landing speed. Now, total pitch and rotor thrust are increased to reduce landing speed to zero unless touchdown. |
| Method of rotorcraft no-run takeoff with autorotating rotor and wing / 2514012 Rotor is spinned at minimum common pitch to preset rpm at starting. Then, craft vertical lift is performed till undercarriages wheels rotation by increase of common pitch and rotor thrust. Thereafter, it is accelerated by changing the engine control levers into takeoff position till preset takeoff speed and altitude. |
FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to landing of rotorcraft. Proposed method consists in that, first, preset speed is selected at glide path slope. Then, total pitch of the rotor is selected. Then, reverse is actuated of engine reversing devices are activated depending upon engine type at preset altitude above landing ground to brake the rotorcraft and to reduce landing speed. Now, total pitch and rotor thrust are increased to reduce landing speed to zero unless touchdown.
EFFECT: landing without alighting run.
The claimed invention relates to the field of aviation.
Rotorcraft UAV with windmilling rotor and wing on the principle of creating lift at low flight speeds refers to , which is an intermediate type of aircraft between a helicopter and an airplane. In this connection it is expedient to consider the existing methods of planting, applied on a helicopter, plane and .
There is a method of vertical landing of the helicopter. On the glide path planning pilot sets the given speed. At a given height above the landing site of the pilot, influencing the control levers on the collective and cyclic step rotor system, applies the brakes helicopter and produces hang over the landing pad. After this, smooth reduction of the collective pitch of the main rotor pilot controls reduction and landing of a helicopter [1].
For helicopter unlike aircraft, there are no such concepts as speed and critical stall. The necessary stability of the device at low speed flight, including at zero its meaning is provided by the rotating rotor and its handling at the expense of the impacts of the pilot levers of management of the collective and cyclic step rotor.
Also known way to landing. On the glide path planning pilot sets the given speed. Method of planting includes the stage of flight at glide path planning with a given height above the level of the end of the runway on landing and mileage aerodrome to a complete stop. The specified flight stage involves several stages: alignment, maturing, and landing [2, .441]. The less speed of the plane, the less its landing speed and length of the race.
To implement the deceleration of the aircraft after landing and reduction of run using wheel brakes chassis. In addition, to reduce mileage may also apply depending on the type of aircraft propulsion reversing device jet engines or reverse propellers. Use on a plane-80GP wheel brakes chassis and reverse propellers after landing on runway allowed to obtain the mean free path 280 m [3].
Method of planting autogyro has no fundamental differences from the way the landing of the plane. On the glide path planning pilot also establishes a given speed. Method of planting includes the stage of flight at glide path planning with a given height above the landing site to the landing and the short run to a complete stop. The main advantage of the autogyro: minimum () speed and smaller size in comparison with the plane landing distance [2 : 34]. Unlike the autogyro is much smaller values of the landing speed and length of run. In addition, the autogyro, as the helicopter, rotating rotor provides the necessary stability and controllability at much lower speeds stages of the implementation of landing compared to an airplane.
The technical purpose of the claimed invention is a way of landing without running a rotorcraft with windmilling rotor and wing, which for braking a rotorcraft at glide path planning and reduce landing speed to zero by the time of landing used, depending on the type of power plant reversible propellers or reversing device engines and pitch of the main rotor to increase its thrust through the available stock of kinetic energy.
The technical result of the method of planting without mileage aircraft with the windmilling rotor and wing is achieved by setting the specified speed on the glide path planning, then install the specified pitch of the main rotor, after this include, depending on the type of power plant reverse propellers or reversing device engines at a given height relative to the surface of the landing site for braking apparatus and reduce landing speed, then before the end of the braking step and increase the overall thrust of the main rotor to reduce landing speed of the device up to a zero value to the moment of touch wheel chassis surface area.
Example of the method for landing without running a rotorcraft with windmilling rotor and wing consists in the following:
- establish a set speed on the glide path planning;
- then establish a given pitch of the main rotor to provide the highest possible frequency of its rotation and adequate supply of kinetic energy;
- after this include, depending on the type of power plant reverse propellers or reversing device engines at a given height relative to the surface of the landing site for braking apparatus and reduce landing speed. The necessary stability of the device at low speeds provide through the revolving rotor, and its handling at the expense of the impacts of the pilot levers of management of the collective and cyclic step rotor;
- then, before the end of the braking step and increase the overall thrust of the main rotor to reduce landing speed of the device up to a zero value by the moment of touch wheel chassis surface area.
The necessary increase in thrust rotor reach through the use of stored kinetic energy.
Analysis conducted by the applicant prior art has shown that the set of essential features of the claimed technical solutions is a new and meets the condition of patentability of the invention.
Sources of information
1. Instructions to the crew of the Mi-4A with engine ASH-82B, military publishing house of the Ministry of defense of the USSR, Moscow, 1972(p.60, 61).
2. Svishchev G.P. aviation, encyclopedia. Scientific publishing house «the Great Russian encyclopedia», Central Aerohydrodynamic Institute, Moscow, 1994
3. M.P. Simonov, Litvinov GA Multifunctional aircraft for local and regional air lines-80GP. Magazine « N91, Publishing house «mechanical engineering», Moscow, 1999(p.14).
Way to landing without running a rotorcraft with windmilling rotor and wing, which consists in the installation of the specified speed on the glide path planning, wherein the set specified pitch of the main rotor, then depending on the type of power plant reverse propellers or reversing device engines at a given height relative to the surface of the landing site for braking apparatus and reduce landing speed, then before the end of the braking step and increase the overall thrust of the main rotor to reduce landing speed of the device up to a zero value by the moment of touch wheel chassis surface area.