阅读说明：本技术 一种单组旋翼无反扭矩尾桨直升机的动力系统 (Power system of single-group rotor wing non-reactive torque tail rotor helicopter ) 是由 王泽民 于 2019-12-11 设计创作，主要内容包括：针对传统直升飞机利用反扭矩尾浆,共轴双组旋翼相互反转来平衡机体旋转扭矩方法存在：机尾过长,动力传动距离远,速度比较慢,机动性比较差等一些实际不足,本发明提出的一种单组旋翼无反扭矩尾桨直升机的动力系统以及加推力桨或倾转推力桨直升机的动力系统,替代传统直升飞机的反扭尾桨、共轴双组旋翼中的一组旋翼来平衡机体旋转扭矩、提高直升机的飞行速度以及机动性。(The method for balancing the rotating torque of the helicopter body by utilizing the anti-torque tail rotor and mutually reversing the coaxial double-rotor-group rotors by aiming at the traditional helicopter comprises the following steps: the invention provides a power system of a helicopter with a single-group rotor wing and a tail rotor without back torque and a power system of a helicopter with a thrust propeller or a tilt thrust propeller, which have the practical defects of long tail, long power transmission distance, low speed, poor maneuverability and the like.)

1. A power system of a single-set rotor non-reaction torque tail rotor helicopter comprises: organism, engine, no oar formula torque balance ware, single group rotor, characterized by: the helicopter is characterized in that an engine body is connected with an upper part of the engine, a transmission mechanism is connected with the upper part of the engine, the lower part of the engine (F) is connected with a combined speed reducer (ZH) in the prior art, the combined speed reducer (ZH) is provided with one to five output shafts which rotate in the opposite direction of the rotation direction of a rotor shaft (YZ) and have the axis line different from the rotation direction of the rotor shaft (YZ), the output shaft of the combined speed reducer (ZH) is connected with a load mechanism which is connected with the output shaft of the combined speed reducer (ZH) and a shell of the combined speed reducer, and a shell (A) of the combined speed reducer is connected.

2. The power system of a single set of rotor wing non-reactive torque tail rotor helicopter as claimed in claim 1, wherein: the combined speed reducer (ZH) is composed of a planetary speed reduction unit and a parallel shaft type speed reduction unit, one to five power output shafts take a middle gear in the parallel shaft type speed reduction unit as a center, teeth on the periphery of the power output shafts are meshed with one to five output gears or output gear sets uniformly distributed at 360 degrees, the output gears or the output gear sets are connected with an output shaft, and the combined double-shaft output speed reducer (ZH) in the combined speed reducer is taken as an example on the principle that the rotation direction of the output gear or the output gear sets is opposite to the rotation direction of a rotor shaft (YZ): the lower output shaft (1) of the engine is connected with a sun gear (2) of a combined double-shaft output speed reducer, the sun gear (2) is connected with at least three star gears (3-3) with the angle of 120 degrees, the star gears (3-3) are connected with a planetary gear shaft (4-3) and a gear ring (5), the planetary gear shaft (4-3) is connected with a star frame (6), and the star frame (6): firstly, when the combined type speed reducer (ZH) is selected to output by one shaft and two shafts, the star frame (6) is connected with the middle shaft (7), secondly, when the combined type speed reducer (ZH) is selected to output by three to five shafts, the star frame (6) can be directly connected with the middle gear (9), the star frame (6) is connected with the middle shaft (7), two ends of the middle shaft (7) are connected with the bearings (8) and (10), the bearings (8) and (10) are connected with the shell (A), the middle part of the middle shaft (7) is connected with the middle gear (9), the left side of the middle gear (9) is connected with the output gear (15), the output gear (15) is connected with the output shaft (Z16), two ends of the output shaft (Z16) are connected with the bearings (17) and (18), the bearings (17) and (18) are connected with the shell (A), the right side of the middle gear (9) is connected with the, the two ends of the output shaft (Z12) are connected with bearings (13) and (14) of the output shaft, the bearings (13) and (14) are connected with a shell (A), the structure is connected with an engine (F) in a downward connection mode, the upward connection mode is that a combined double-shaft output speed reduction (ZH) machine is arranged on the upper portion of an upper transmission mechanism (SD), a sun gear (2) of the combined double-shaft output speed reduction (ZH) machine is connected to a rotor shaft (YZ) in a sleeved mode, a star frame (6) and a middle gear (9) of the combined double-shaft output speed reduction (ZH) machine are connected with the rotor shaft (YZ) through the bearings in a sleeved mode by taking the rotor shaft.

3. The power system of a single-set rotor anti-torque tail rotor helicopter as claimed in claim 1 or 2, wherein: the load mechanism comprises: a radial plunger type mechanism (J) in the medium pressure technology, various clutches, couplers, coupling type couplers in the power transmission technology, a disc type brake mechanism (D) in the brake technology, or a combined type load mechanism (DJ) consisting of two mechanisms in the brake technology, is particularly applied to one mechanism in the load mechanisms,

the radial injection type load mechanism (J) is particularly applied to the helicopter power system: firstly, at least two cylinder bodies (24-4) are respectively and uniformly distributed on a shell (A) of the combined double-shaft output speed reducer by taking output shafts (Z16) and (Z12) as centers, a plunger (22-4) is connected in the cylinder body (24-4) in a sliding manner, a spring (23-4) is connected between the top in the cylinder body (24-4) and the outer end of the plunger (22-4), and the inner end of the plunger (22-4) is connected with the output shafts (Z16) and (Z12) of the combined double-shaft output speed reducer, namely: the disc cam (21-2) on the input shaft (Z19-2) of the radial plunger type load mechanism (J) is in sliding connection, N ascending and descending fillets formed by convex-concave bodies are uniformly distributed on the axial circumferential surface of the disc cam (21-2) in the radial direction, when the disc cam (21-2) rotates, a plunger (22-4) in sliding connection with the disc cam (21-2) is forced to move outwards along the longitudinal direction of a cylinder body (24-4) under the action of the ascending fillets, the plunger (22-4) moves outwards to press a compression spring (23-4) and a medium, the plunger (22-4) enables the plunger (22-4) to move back and suck the medium along with the descending fillets by the compression spring (23-4) after the ascending fillets reach the top points, and the spring (23-4) enables the plunger (22-4) to be always in sliding connection with the cam (21-2) in the reciprocating process, secondly, the top of a cylinder body (24-4) is connected with a medium pressure storage tank, a medium with certain pressure is arranged in the medium pressure storage tank, a control mechanism (25-4) amplifies a control valve hole after a plunger (22-4) reaches a top point, a medium back pressure plunger (22-4) with certain pressure presses the control valve to be closed after the back pressure plunger to follow a descending fillet of a cam (21-2) to descend to a low point, the plunger (22-4) starts to move outwards to compress the medium, the end part of the cylinder body (24-4) is connected with the medium inlet and outlet control mechanism (25-4), the control mechanism (25-4) controls an electromagnetic valve by the control mechanism according to the change of the rotating torque of a machine body (JT), the pressure in the cylinder body (24-4) is controlled by controlling the medium output flow in the cylinder body (24-4), so that the shell (A) of the combined double-shaft output speed reducer,

the disc brake load mechanism (D) is applied to the helicopter power system specifically: at least one set of fixed or floating brake calipers (32-4) is arranged on a combined double-shaft output speed reducer shell (A) by taking output shafts (16) and (12) as centers, wherein the output shafts (16) and (12) are as follows: the end part of an input shaft (Z26-2) of the disc type load mechanism (D) is connected with a brake disc (28-2) of the disc type brake load mechanism (D), the brake disc (28-2) is connected with a friction block (29-8), the friction block (29-8) is connected with a piston (30-8), the piston (30-8) is connected with a cylinder body (31-8), the cylinder body (31-8) is connected with a brake caliper (32-4), the cylinder body (31-8) is connected with a medium inlet and outlet hole (33-4), the medium inlet and outlet hole (33-4) is connected with a medium pressure control mechanism, the medium pressure control mechanism controls the medium pressure transmitted to the cylinder body (31-8) by a pressure source according to the change of the rotating torque of a machine body (JT), so that the piston (30-8) acts on the friction block (29-8) and is applied to the brake disc (28-2) The friction pressure of the combined double-shaft output speed reducer enables the shell (A) of the combined double-shaft output speed reducer to generate reaction torque,

the combined load mechanism (DJ) of the radial injection plug type mechanism and the disc type brake mechanism is applied to the helicopter power system in particular: at least two cylinder bodies (38-2) are respectively and uniformly distributed on the shell (A) of the combined double-shaft output speed reducer by taking the output shafts (16) and (12) as centers, and the output shafts (16) and (12) are as follows: the middle part of an input shaft (Z34-2) of the combined load mechanism (DJ) is connected with a bearing (41-2) connected with a shell (A) and a cam (35-2) of the combined load mechanism, the cam (35-2) is connected with a plunger (36-4), the plunger (36-4) is connected with a cylinder body (38-4), a spring (37-4) is connected between the cylinder body (38-4) and the plunger (36-4), the cylinder body (38-4) is connected with a medium inlet and outlet control mechanism (39-4), the end part of the input shaft (Z34-2) is connected with a brake disc (42-2), the brake disc (42-2) is connected with a friction block (43-8), the friction block (43-8) is connected with a piston (45-8), the piston (45-8) is connected with a cylinder body (44-8), the cylinder body (44-8) is connected with a fixed or floating brake caliper (46-4), the cylinder body (44-8) is connected with a medium inlet and outlet hole (47-4), the medium inlet and outlet hole (47-4) is connected with a medium pressure control mechanism, and the two mechanisms are controlled: one of the two can be fixedly arranged, the other can be controlled at any time along with the change of the torque of the machine body, the specific actuating mechanism adopts the traditional medium pressure technology, the control instruction is born by the attitude sensor, the computer and the instruction amplification component, and the manual control is used as a standby combined control mechanism.

4. A power system of a single-set rotor non-reaction torque tail rotor helicopter comprises: organism, engine, no oar formula torque balance ware, single group rotor characterized by: the helicopter in the prior art is characterized in that the engine body (JT) is connected with an engine (F), the engine (F) is vertically connected with a main reducer (ZJ), a main reducer (ZJ) is connected with a single group of rotors (Y), the lower part of the main reducer (ZJ) is connected with a combined reducer (ZH1), the combined reducer (ZH1) is provided with one to five output shafts which rotate in the opposite directions of the rotation directions of the rotor shafts and the rotor shaft and have the axis difference with the rotor shaft, the output shaft of the combined reducer (ZH1) is connected with a load mechanism of the combined reducer (ZH1), and the combined reducer housing (A1) is connected with the engine body (JT1) and forms relative balance torque with the engine body (JT 1); on the basis of the scheme, a power transmission system (WD) of a counter-torque tail rotor of the helicopter in the prior art is used for connecting a fixed thrust propeller or a tilting thrust propeller (TJ) on the tail of the helicopter.

5. The power system of a single set of rotor wing non-reaction torque tail rotor helicopter as claimed in claim 4, wherein: the combined type speed reducer (ZH1) is composed of a planetary type speed reducing unit and a parallel shaft type speed reducing unit, wherein one to five power output shafts take a middle gear (56) in the parallel shaft type speed reducing unit as a center, teeth on the periphery of the middle gear are meshed with one to five output gears or output gear sets in a 360-degree uniform distribution mode, the output gears or the output gear sets are connected with an output shaft, and the combined type double-shaft output speed reducer (ZH1) in the combined type speed reducer is taken as an example on the principle that the rotation direction of the output gear or the output gear sets is opposite to the rotation direction of a rotor shaft (YZ): the combined double-shaft output speed reducer (ZH1) and the main speed reducer (ZJ) have two connection modes, wherein the connection mode (L1) is as follows: the upper end of an input shaft (48) is connected with a main speed reducer shaft (ZO), the middle of the input shaft is connected with a bearing (49) connected with a shell, the lower end of the input shaft is connected with a sun gear (50) of a combined speed reducer, the sun gear (50) is connected with at least three planetary gears (51-3) which are 120 degrees, the planetary gears (51-3) are connected with a planetary gear shaft (52-3) and a gear ring (53), the planetary gear shaft (53-3) is connected with a planet carrier (54), and the planet carrier (54): 1. when the combined type speed reducer (ZH1) is selected to output from a first shaft and a second shaft, the star frame (54) is connected with the middle shaft (55), 2, when the combined type speed reducer (ZH) is selected to output from a third shaft to a fifth shaft, the star frame (54) can be directly connected with the middle gear (56), the star frame (54) is connected with the middle shaft (55), two ends of the middle shaft (55) are connected with the bearings (57) and (58), the bearings (57) and (58) are connected with the shell (A1), the middle part of the middle shaft (55) is connected with the middle gear (56), the left side of the middle gear (56) is connected with the output gear (59), the output gear (59) is connected with the two ends of the output shaft (Z60) and the output shaft (Z60) and is connected with the bearings (61) and (62), the bearings (61) and (62) are connected with the shell (A1), the right side of the middle gear (56) is, (66) Bearings (65), (66) are connected to a housing (A1) in a manner (L2): when the connection mode (L2) is implemented, a speed reduction gear is respectively added between a middle gear (56) and a left output gear (59) and between the middle gear (56) and a right output gear (63) to ensure that the rotation direction of an output shaft is opposite to the rotation direction of a rotor shaft (YZ), the connection is that a combined speed reducer (ZH1) and a load mechanism thereof are arranged above a main speed reducer (ZJ) in a way that the upper end of the input shaft (48) is connected with the middle gear (01) and the middle gear (56) is connected with the rotor shaft (YZ) through a bearing by taking the rotor shaft (YZ) as the center, a sun gear (50) is sleeved on the rotor shaft (YZ), a planet carrier (54) and the middle gear (56) are connected with the rotor shaft (YZ) through a bearing by taking the rotor shaft (YZ) as the center, and the positions of other output gears are the same as the lower end connection.

6. The power system of a single-set rotor anti-torque tail rotor helicopter as claimed in claim 4 or 5, wherein: the load mechanism comprises: the radial injection-plug type mechanism (JX) in the medium pressure technology, various clutches and couplers in the power transmission technology, the disc brake mechanism (ZD) in the coupling type coupling brake technology or one of the combined mechanisms (DJ1) of the two mechanisms are specifically applied,

the radial injection type load mechanism (JX) is applied to the reaction torque in the helicopter power system in particular: at least two cylinder bodies (72-4) are uniformly distributed on a shell (A1) of the combined double-shaft output speed reducer by taking an output shaft (Z60) and an output shaft (Z64) as the center, a plunger (70-4) is connected in the cylinder body (72-4) in a sliding manner, a spring (71-4) is connected between the inner top of the cylinder body (72-4) and the outer end of the plunger (70-4), and the inner end of the plunger (70-4) is connected with the output shafts (Z60) and (Z64) of the combined double-shaft output speed reducer, namely: the disc cam (69-2) on the input shaft (Z67-2) of the radial plunger type load mechanism is in sliding connection, N ascending and descending fillets formed by convex-concave bodies are uniformly distributed on the axial circumferential surface of the disc cam (69-2) in the radial direction, the disc cam (69-2) forces a plunger (70-4) in sliding connection with the disc cam (69-2) to move outwards along the longitudinal direction of a cylinder body (72-4) under the action of the ascending fillets when rotating, the plunger (70-4) moves a compression spring (71-4) and a medium outwards, the plunger (70-4) enables the plunger (70-4) to move back and suck the medium along with the descending fillets by the compressed spring (71-4) after the compression medium and the ascending fillets reach the top points, and the sliding connection state of the plunger (70-4) and the cam (69-2) is always kept by the spring (71-4) in the reciprocating process, secondly, the top of the cylinder body (72-4) is connected with a medium pressure storage tank, a medium with certain pressure is arranged in the medium pressure storage tank, the control mechanism (73-4) amplifies the control valve hole after the plunger (70-4) reaches the top point, the medium back pressure plunger (70-4) with certain pressure presses the control valve to be closed after the round angle descends to the low point along with the descending cam (69-2), the plunger (70-4) begins to move outwards to compress the medium, the end part of the cylinder body (72-4) is connected with the medium inlet and outlet control mechanism (73-4), the control mechanism (73-4) controls the electromagnetic valve by the control mechanism according to the change of the rotating torque of the machine body (JT), the pressure in the cylinder body (72-4) is controlled by controlling the medium output flow in the cylinder body (72-4), so that the combined double-shaft output speed reducer shell (A1) generates reaction torque.

The disc brake load mechanism (ZD) is applied to the helicopter power system specifically: at least one set of fixed or floating brake calipers (80-4) is respectively arranged on a combined double-shaft output speed reducer shell (A1) by taking an output shaft (Z60) and an output shaft (Z64) as a center, and the output shafts (Z60) and (Z64) of the double-shaft output type planetary speed reducer are as follows: the end part of an input shaft (74-2) of the disc brake load mechanism (ZD) is connected with a brake disc (76-2), the brake disc (76-2) is connected with a friction block (77-8), the friction block (77-8) is connected with a piston (78-8), the piston (78-8) is connected with a cylinder body (79-8), the cylinder body (79-8) is connected with a brake caliper (80-4), the cylinder body (79-8) is connected with a medium inlet and outlet hole (81-4), and the medium inlet and outlet hole (81-4) is connected with a medium pressure control mechanism, the medium pressure control mechanism controls the medium pressure transmitted to the cylinder body (79-8) by a pressure source according to the change of the rotating torque of a machine body (JT), so as to control the friction pressure applied to the brake disc (76-2) by the piston (78-8) acting on the friction block (77-8), so that the combined double-shaft output speed reducer shell (A1) generates reaction torque,

the combined loading mechanism (JD1) of the radial plug type mechanism and the disc type brake mechanism is applied to the helicopter power system: at least two cylinder bodies (87-2) are respectively and uniformly distributed on a combined double-shaft output speed reducer shell (A1) by taking output shafts (Z60) and (Z64) as centers, and the output shafts (Z60) and (Z64) of the combined double-shaft output speed reducer are as follows: an input shaft (Z82-2) of the combined load mechanism (JD1) is connected with a bearing (89-2) connected with a shell (A1) and a cam (84-2) of the combined load mechanism, the cam (84-2) is connected with an injection plug (85-4), the injection plug (85-4) is connected with a cylinder (87-4), a spring (86-4) is connected between the cylinder (87-4) and the injection plug (85-4), the cylinder (87-4) is connected with a medium inlet and outlet control mechanism (88-4), the end of the input shaft (Z82-2) is connected with a brake disc (90-2), the brake disc (90-2) is connected with a friction block (91-8), the friction block (91-8) is connected with a piston (93-8), and the piston (93-8) is connected with a cylinder (92-8), the cylinder (92-8) is connected with a fixed or floating brake caliper (94-4), the cylinder (92-8) is connected with a medium inlet and outlet hole (95-4), the medium inlet and outlet hole (95-4) is connected with a medium pressure control mechanism, and the two control mechanisms are controlled: one of the two combined control mechanisms can be fixedly arranged, the other one of the two combined control mechanisms can be controlled at any time along with the change of the torque of the machine body, the specific execution mechanism adopts the traditional medium pressure technology, a control instruction is born by an attitude sensing computer and an instruction amplification component, and manual control is used as a standby combined control mechanism.

7. The power system of a single set of rotor wing non-reaction torque tail rotor helicopter as claimed in claim 4, wherein: the power transmission system (WD) utilizing the counter-torque tail rotor of the helicopter in the prior art is connected with a fixed thrust propeller or a tilting thrust propeller (TJ) on the tail, the structure of the fixed flight thrust propeller is composed of a traditional structure, the connection with a machine body (JT1) is a conventional connection mode, and the tilting thrust propeller (TJ) comprises: support (96), tilting arm (97), support (96) connect bearing (105-2), bearing (105-2) are connected and are connected tilting arm (97), tilting arm (97) connect bearing (98), (100), output shaft (99) is connected to bearing (98), (100), output shaft (99) front end connect thrust paddle (TJ), rear end connecting axle telescopic joint (101), ball cage or dual coupling (102) are connected to axle telescopic joint (101), ball cage or dual coupling (102) connect power input shaft (104), input shaft (104) connect bearing (103).

8. The power system of a helicopter with fixed or tilting flight thrusting propellers with a single set of rotors according to claim 7, characterized in that: the tilting mechanism of the tilting thrust paddle is a cylinder body and a plunger type structure in a hydraulic technology, a motor and a gear type structure are formed, the cylinder body is connected with a supporting seat plunger to be connected with a tilting arm, the plunger extends and contracts to realize tilting of the tilting arm at a left angle of less than 100 degrees, the supporting seat is connected with the motor, the motor is connected with a gear, the gear is connected with a tilting gear, and the tilting arm is connected with the tilting arm through the tilting gear to realize tilting of the tilting arm at a left angle of less than 100 degrees.

The technical field is as follows:

the invention relates to the field of aviation, in particular to a power system of a single-group rotor helicopter.

Background art:

helicopter can appear the organism rotation and lose lift and take place the crash accident in the use, for balanced organism rotation moment of torsion, traditional helicopter adopts and installs variable pitch screw additional at its afterbody to balance organism rotation moment of torsion. In order to reduce the power consumption of the balanced organism rotation moment of tail rotor, adopt extension tail to increase the lever between rotor main shaft to the tail rotor and act on the distance, reduce the power consumption of tail rotor, and in order to ensure the rotatory safety of rotor, need certain safe distance between rotor and the tail rotor, consequently lead to traditional helicopter tail overlength, the power transmission distance of tail rotor is far away, tail structure volume ratio is handed down, high in weight, the flying speed is slower, the maneuverability is than poor, owing to there is the tail rotor: the tail slurry has high noise and is easy to hurt ground personnel, and the tail slurry is easy to collide with other objects and damage, so that the crash accident occurs. The traditional helicopter which adopts the mutual reverse rotation of the coaxial double-group rotor wings to balance the rotating torque of the helicopter body also has the defects that a certain safety distance is needed between the coaxial double-group rotor wings, so that the main shaft is too long, the flight resistance is increased, the flight speed is limited, the maneuvering performance is poor, the double-group rotor wing mechanism is complex, and the control difficulty is high. The traditional helicopter adopting the duct type tail slurry and generating the active airflow to be reversely ejected from the tail part still has the defects of long tail, large structural volume, high weight, high resistance, low speed, poor maneuverability and poor efficiency.

The purpose of the invention is as follows:

the invention provides a power system of a single-group rotor wing non-reactive torque tail rotor helicopter, which solves the defects in the prior art, and the specific technical scheme is as follows:

the invention content is as follows:

a power system of a single-set rotor non-reaction torque tail rotor helicopter comprises: the helicopter in the prior art is characterized in that the lower part of the engine is connected with a combined speed reducer, the combined speed reducer is provided with one to five output shafts which rotate in the direction opposite to the rotation direction of a rotor shaft and have the axis line different from the rotor shaft, the output shaft of the combined speed reducer is connected with a load mechanism which is in the same shell with the combined speed reducer, and the shell of the combined speed reducer is connected with the helicopter body and forms relative balance torque with the helicopter body.

The utility model provides a single unit rotor does not have driving system of reaction torque tail-rotor helicopter, combination formula speed reducer constitute by planetary reduction unit and parallel shaft type reduction unit, one to five power output shafts be with the meshing one to five output gears or output gear group of taking the well gear among the parallel shaft type reduction unit as its all around tooth 360 degrees equipartitions of center, output gear or output gear group connect the output shaft and regard its direction of rotation and rotor shaft direction of rotation as the principle, use the combination formula biax output speed reducer that includes in the combination formula speed reducer as the example: the lower output shaft of the engine is connected with a first sun gear of the combined double-shaft output speed reducer, the first sun gear is connected with at least three first, second and third planetary gears which are 120 degrees mutually, the first, second and third planetary gears are connected with a first, second and third planetary gear shafts and a gear ring, the first, second and third planetary gear shafts are connected with a star frame, and the star frame: the star frame is connected with a middle gear when the selective combined type speed reducer is output by a first shaft and a second shaft, the star frame can be directly connected with the middle gear when the selective combined type speed reducer is output by three to five shafts, the star frame is connected with the middle shaft, two ends of the middle shaft are connected with a first bearing and a second bearing, the first bearing and the second bearing are connected with a shell, the middle gear is connected with the middle gear, the left side of the middle gear is connected with a first output gear, the first output gear is connected with a first output shaft, two ends of the first output shaft are connected with a first bearing and a second bearing, the first bearing and the second bearing are connected with the shell, the right side of the middle gear is connected with a second output gear, the second output gear is connected with a second output shaft, two ends of the second output shaft are connected with a third bearing and a fourth bearing, the third bearing and the fourth bearing are connected with the shell, the, the upper part of the transmission mechanism is connected with a rotor shaft through a set of sun gears, a star frame and a middle gear of the transmission mechanism are connected with the rotor shaft sleeve through a bearing by taking the rotor shaft as the center, and the positions of other output gears are the same as those of the lower part.

A power system for a single-rotor, non-reactive-torque tail rotor helicopter, said load mechanism comprising: the radial filling-plug type mechanism in the medium pressure technology, various clutches, couplers, coupling couplers and disc brake mechanism in the power transmission technology or the combined load mechanism consisting of two mechanisms are specifically applied to one mechanism in the load mechanism,

the radial injection type load mechanism is specifically applied to the helicopter power system: the combined double-shaft output speed reducer is characterized in that at least two cylinder bodies are uniformly distributed on a shell of the combined double-shaft output speed reducer by taking an output shaft I and an output shaft II as centers respectively, a plunger piston is connected in the cylinder bodies in a sliding manner, a spring is connected between the top in the cylinder body and the outer end of an injection plug, the inner end of the plunger piston is connected with a disc cam connected to the output shaft I and the output shaft II of the combined double-shaft output speed reducer in a sliding manner, N ascending and descending circular beads formed by convex-concave bodies are uniformly distributed on the axial circumferential surface of the disc cam in the radial direction, the plunger piston connected with the disc cam in a sliding manner is forced to move outwards along the longitudinal direction of the cylinder body under the action of the ascending circular bead when the disc cam rotates, the plunger piston moves outwards to compress the spring and the medium, the plunger piston is compressed after the, the top of the cylinder body is connected with a medium pressure storage box, a medium with certain pressure is arranged in the medium pressure storage box, the control mechanism amplifies the control valve hole after the plunger reaches the vertex, the medium with certain pressure returns to the pressure plunger to press the plunger to descend to a low point along with the descending fillet of the cam and then control the valve to be closed, the plunger begins to move outwards to compress the medium, the end of the cylinder body is connected with the medium inlet and outlet control mechanism, the control mechanism controls the electromagnetic valve through the control mechanism according to the change of the rotating torque of the machine body, and the pressure in the cylinder body is controlled by controlling the medium output flow in the cylinder body, so that the combined double-shaft output speed reducer.

The disc type braking load mechanism is applied to the helicopter power system specifically: at least one group of fixed or floating brake calipers is arranged on a combined double-shaft output speed reducer shell by taking an output shaft I and an output shaft II as centers, the two ends of the output shaft I and the output shaft II are connected with a brake disc of a disc type brake load mechanism, the brake disc is connected with a friction block, the friction block is connected with a piston, the piston is connected with a cylinder body, the cylinder body is connected with the brake calipers, the cylinder body is connected with a medium inlet and outlet hole, the medium inlet and outlet hole is connected with a medium pressure control mechanism, the medium pressure control mechanism controls the friction pressure applied to the brake disc by the friction block by the piston through controlling the medium pressure transmitted to the cylinder body by a pressure source according to the change of the rotating torque of the machine body, so that the combined,

the combined load mechanism of the radial plug-injection type mechanism and the disc type braking mechanism is applied to the helicopter power system specifically: at least two cylinder bodies are respectively and uniformly distributed on a shell of the combined double-shaft output speed reducer by taking an output shaft I and an output shaft II as centers, the middle parts of the output shaft I and the output shaft II are connected with a bearing connected with the shell and a cam I and a cam II of a combined load mechanism, the cam is connected with an injection plug, the injection plug is connected with the cylinder body, a spring is connected between the cylinder body and the injection plug, the cylinder body is connected with a medium inlet and outlet control mechanism, the two end parts of the output shaft I and the output shaft II are connected with brake discs, the brake discs are connected with friction blocks, the friction blocks are connected with pistons, the pistons are connected with the cylinder body, the cylinder body is connected with a fixed or floating brake caliper, the cylinder body is connected with a medium inlet and outlet, the medium inlet and outlet: one of the two can be fixedly arranged, the other can be controlled at any time along with the change of the torque of the machine body, the specific actuating mechanism adopts the traditional medium pressure technology, the control instruction is born by the attitude sensor, the computer and the instruction amplification component, and the manual control is used as a standby combined control mechanism.

A power system of a single-set rotor non-reaction torque tail rotor helicopter comprises: the helicopter is characterized by comprising a helicopter body, an engine, a paddle-free torque balancer and a single-group rotor wing, wherein the engine is connected with the engine, the engine is vertically connected with a main reducer, the main reducer is connected with the single-group rotor wing, the helicopter in the prior art is characterized in that the lower part of the main reducer is connected with a combined speed reducer, the combined speed reducer is provided with one to five output shafts which rotate in the opposite directions of the rotation direction and the rotation direction of a rotor wing shaft and have the axis different from the rotor wing shaft, the output shaft of the combined speed reducer is connected with a load mechanism which is the same with the combined speed reducer in a shell, and the shell of the combined; on the basis of the scheme, a power transmission system of the counter-torque tail rotor of the helicopter in the prior art is utilized to connect a fixed thrust propeller or a tilting thrust propeller on the tail of the helicopter.

The utility model provides a single unit rotor does not have driving system of reaction torque tail-rotor helicopter, combination formula speed reducer constitute by planetary reduction unit and parallel shaft type reduction unit, one to five power output shafts be with the meshing one to five output gears or output gear group of taking the well gear among the parallel shaft type reduction unit as its all around tooth 360 degrees equipartitions of center, output gear or output gear group connect the output shaft, use its rotation direction and rotor shaft rotation direction as the principle, use the combination formula biax output speed reducer that includes in the combination formula speed reducer as the example: the combined double-shaft output speed reducer and the main speed reducer have two connection modes, namely a first connection mode: the upper end of an input shaft I is connected with a main shaft of a main speed reducer, the middle part of the input shaft I is connected with a bearing connected with a shell, the lower end of the input shaft I is connected with a sun gear I of a combined speed reducer, the sun gear I is connected with at least three planetary gears I, II and III which are 120 degrees, the planetary gears I, II and III are connected with planetary gear shafts I, II and III and a gear ring, the planetary gear shafts are connected with a star frame, and the star frame: 1. the star frame is connected with the middle shaft when the combined type speed reducer is output by a first shaft and a second shaft, 2, the star frame can be directly connected with the middle gear when the combined type speed reducer is output by a third shaft to a fifth shaft, the star frame is connected with the middle shaft, two ends of the middle shaft are connected with a first bearing and a second bearing, the first bearing and the second bearing are connected with the shell, the middle part of the middle shaft is connected with the middle gear, the left side of the middle gear is connected with a first output gear, the first output gear is connected with a first output shaft, two ends of the first output shaft are connected with a first bearing and a second bearing, the first bearing and the second bearing are connected with the shell, the right side of the middle gear is connected with a second output gear, two ends of the second: when the second connection mode is implemented, a reduction gear is added between the middle gear and the left output gear I, the middle gear and the right output gear II respectively to enable the rotation direction of the output shaft to be opposite to the rotation direction of the rotor shaft, the connection is connected with the lower portion of the main speed reducer, the combined speed reducer and a load mechanism of the combined speed reducer are arranged above the main speed reducer, the sun gear is connected to the rotor shaft in a sleeved mode, the star frame and the middle gear are connected with the rotor shaft sleeve through bearings by taking the rotor shaft as the center, and the positions of other output gears are the same as those of the lower portion.

A power system for a single-rotor, non-reactive-torque tail rotor helicopter, said load mechanism comprising: the radial filling-plug type mechanism in the medium pressure technology, various clutches, couplers, coupling couplers, disc brake mechanisms in the brake technology or one mechanism in the combined mechanism of the two mechanisms in the prior art of power transmission are specifically applied,

the radial injection type load mechanism is specifically applied to the helicopter power system: the combined double-shaft output speed reducer is characterized in that at least two cylinder bodies are uniformly distributed on a shell of the combined double-shaft output speed reducer by taking a first output shaft and a second output shaft as centers respectively, a plunger is connected in the cylinder bodies in a sliding manner, a spring is connected between the inner top of each cylinder body and the outer end of a filling plug, the inner end of each plunger is connected with a disc cam connected to the first output shaft and the second output shaft of the combined double-shaft output speed reducer in a sliding manner, a first cam and a second cam are connected in a sliding manner, N ascending and descending fillets formed by convex-concave bodies are uniformly distributed on the axial circumferential surface of each disc cam in the radial direction, the plungers in sliding connection with the disc cams are forced to move outwards along the longitudinal direction of the cylinder bodies under the action of the ascending fillets when the disc cams rotate, the plungers move compression springs and media outwards, the plungers enable, secondly, the top of the cylinder body is connected with a medium pressure storage tank, a medium with certain pressure is arranged in the medium pressure storage tank, the control mechanism amplifies the control valve hole after the plunger reaches the vertex, the medium with certain pressure returns to the pressure plunger to press the plunger to descend to the low point along with the descending fillet of the cam and then control the valve to close, the plunger begins to move outwards to compress the medium, the end part of the cylinder body is connected with the medium inlet and outlet control mechanism, the control mechanism controls the electromagnetic valve by the control mechanism according to the change of the rotating torque of the machine body, the pressure in the cylinder body is controlled by controlling the medium output flow in the cylinder body, so that the shell of the combined double-,

the disc type braking load mechanism is applied to the helicopter power system specifically: at least one group of fixed or floating brake calipers are respectively arranged on a combined double-shaft output speed reducer shell by taking an output shaft I and an output shaft II as centers, the first end and the second end of the output shaft I and the output shaft II of the double-shaft output planetary speed reducer are connected with brake discs, the brake discs are connected with friction blocks, the friction blocks are connected with pistons, the pistons are connected with cylinder bodies, the cylinder bodies are connected with brake calipers, the cylinder bodies are connected with medium inlet and outlet holes, the medium inlet and outlet holes are connected with a medium pressure control mechanism, the medium pressure control mechanism controls the friction pressure applied to the brake discs by the friction blocks by the pistons through controlling the medium pressure transmitted to the cylinder bodies by a pressure source according to the change of the rotating torque of a machine body, so that the,

the combined load mechanism of the radial plug-injection type mechanism and the disc type braking mechanism is applied to the helicopter power system specifically: at least two cylinder bodies are respectively and evenly distributed on the shell of the combined double-shaft output speed reducer by taking the first output shaft and the second output shaft as the center, the first and second output shafts of the combined double-shaft output speed reducer are connected with a bearing connected with the shell and a first and second cams of the combined load mechanism, the first cam and the second cam are connected with a plunger, the plunger is connected with a cylinder body, a spring is connected between the cylinder body and the plunger, the cylinder body is connected with a medium inlet and outlet control mechanism, one end and two ends of an output shaft of the double-shaft output type planetary reducer are connected with a brake disc, the brake disc is connected with a friction block, the friction block is connected with a piston, the piston is connected with a cylinder body, the cylinder body is connected with a fixed or floating brake caliper, the cylinder body is connected with a medium inlet and outlet hole, the medium inlet and outlet hole is connected with a medium pressure control mechanism, and the two control mechanisms are controlled: one of the two combined control mechanisms can be fixedly arranged, the other one of the two combined control mechanisms can be controlled at any time along with the change of the torque of the machine body, the specific execution mechanism adopts the traditional medium pressure technology, a control instruction is born by an attitude sensing computer and an instruction amplification component, and manual control is used as a standby combined control mechanism.

The utility model provides a single unit rotor does not have driving system of anti-torque tail-rotor helicopter, the driving system who utilizes prior art helicopter anti-torque tail-rotor, connect fixed thrust propeller or the thrust propeller that verts on the tail, the structure of fixed thrust propeller constitute by traditional structure and be conventional connected mode with being connected of organism, the thrust propeller that verts constitute and include: support, the arm that verts, the support connect bearing one, two, bearing one, two connect and connect the arm that verts the arm connect bearing three, four, the output shaft is connected to bearing three, four, the output shaft front end connect the thrust paddle, rear end connecting axle telescopic joint, axle telescopic joint connect rzeppa or twin coupling, rzeppa or twin coupling connect the power input shaft, input shaft connecting bearing five.

The utility model provides a power system of single unit rotor does not have anti-torque tail-rotor helicopter, the mechanism of verting of distance propeller of verting be with cylinder body and plunger type structure among the hydraulic pressure technique, the motor forms with gear formula structure, through connecting cylinder body supporting seat plunger connection tilting arm, tilting less than 100 degrees about tilting arm is done in the extension and the shrink of plunger, supporting seat connection motor, motor connection gear, gear connection tilting gear, tilting gear connection tilting arm's interlock realizes tilting less than 100 degrees about tilting arm does.

Has the advantages that:

1. the helicopter without the tail rotor and the single group of rotor wings has the advantages that ground personnel can be easily injured by the tail rotor, noise generated by the tail rotor is avoided, the tail rotor collides with other objects to be damaged to cause crash accidents, the tail rotor and the structure weight of the power transmission part of the tail rotor are avoided, the tail can be shortened to the inner side of a rotor disc, and the structure volume and the structure weight of the tail rotor are reduced.

2. The invention can realize single-group rotor without tail rotor, and avoid the defects of double-group rotor.

3. The invention overcomes the defects of larger volume, higher structural weight, larger air-resistance ratio and poor efficiency of a long tail structure due to the fact that the active airflow is generated by washing airflow under a rotor wing and the existence of duct-type tail slurry.

4. The single group of rotors provided by the invention is added with the flight thrust propeller or the horizontal tiltable thrust propeller, so that the flight speed and the maneuverability of the helicopter can be improved.

Description of the drawings:

FIG. 1 is a schematic structural diagram of scheme 1 of the present invention.

Fig. 2 is a schematic diagram of the structure of fig. 1.

Fig. 3 is a schematic diagram of the structure of fig. 1.

Fig. 4 is a schematic diagram of the structure of fig. 1.

FIG. 5 is a schematic structural diagram of scheme 2 of the present invention.

Fig. 6 is a schematic view of the structure of fig. 5.

Fig. 7 is a schematic view of the structure of fig. 5.

Fig. 8 is a schematic view of the structure of fig. 5.

Fig. 9 is a schematic structural view of a tilting thrust paddle according to the embodiment 3 of the present invention.

The specific implementation mode is as follows:

example 1:

a power system of a single-set rotor non-reaction torque tail rotor helicopter comprises: the helicopter is a helicopter in the prior art, the lower part of an engine (F) is connected with a combined speed reducer (ZH), the combined speed reducer (ZH) is provided with one to five output shafts which rotate in the opposite direction to the rotation direction of a rotor shaft (YZ) and have the axis line different from the rotation direction of the rotor shaft (YZ), the output shaft of the combined speed reducer (ZH) is connected with a load mechanism of the combined speed reducer (ZH) and the shell, and the shell (A) of the combined speed reducer is connected with a body (JT) and forms a relative balance torque with the body (JT).

Example 2:

the power system of a single-rotor-wing non-reaction-torque tail rotor helicopter described in embodiment 1, said combined reducer (ZH) is composed of a planetary reduction unit and a parallel-shaft reduction unit, said one to five power output shafts are centered on a middle gear in the parallel-shaft reduction unit, and teeth on the periphery of the power output shafts are uniformly meshed with one to five output gears or output gear sets at 360 degrees, said output gears or output gear sets are connected to an output shaft, and the rotation direction of the output shaft is opposite to the rotation direction of a rotor shaft (YZ), and a combined dual-shaft output reducer (ZH) included in the combined reducer is taken as an example: the lower output shaft (1) of the engine is connected with a sun gear (2) of a combined double-shaft output speed reducer, the sun gear (2) is connected with at least three star gears (3-3) with the angle of 120 degrees, the star gears (3-3) are connected with a planetary gear shaft (4-3) and a gear ring (5), the planetary gear shaft (4-3) is connected with a star frame (6), and the star frame (6): firstly, when the combined type speed reducer (ZH) is selected to output by one shaft and two shafts, the star frame (6) is connected with the middle shaft (7), secondly, when the combined type speed reducer (ZH) is selected to output by three to five shafts, the star frame (6) can be directly connected with the middle gear (9), the star frame (6) is connected with the middle shaft (7), two ends of the middle shaft (7) are connected with the bearings (8) and (10), the bearings (8) and (10) are connected with the shell (A), the middle part of the middle shaft (7) is connected with the middle gear (9), the left side of the middle gear (9) is connected with the output gear (15), the output gear (15) is connected with the output shaft (Z16), two ends of the output shaft (Z16) are connected with the bearings (17) and (18), the bearings (17) and (18) are connected with the shell (A), the right side of the middle gear (9) is connected with the, the two ends of the output shaft (Z12) are connected with bearings (13) and (14) of the output shaft, the bearings (13) and (14) are connected with a shell (A), the structure is connected with an engine (F) in a downward connection mode, the upward connection mode is that a combined double-shaft output speed reduction (ZH) machine is arranged on the upper portion of an upper transmission mechanism (SD), a sun gear (2) of the combined double-shaft output speed reduction (ZH) machine is connected to a rotor shaft (YZ) in a sleeved mode, a star frame (6) and a middle gear (9) of the combined double-shaft output speed reduction (ZH) machine are connected with the rotor shaft (YZ) through the bearings in a sleeved mode by taking the rotor shaft.

Example 3:

a power system for a single-rotor, non-reactive-torque tail rotor helicopter of embodiment 1 or 2, said load mechanism comprising: a radial plunger type mechanism (J) in the medium pressure technology, various clutches, couplers, coupling type couplers in the power transmission technology, a disc type brake mechanism (D) in the brake technology, or a combined type load mechanism (DJ) consisting of two mechanisms in the brake technology, is particularly applied to one mechanism in the load mechanisms,

the radial injection type load mechanism (J) is particularly applied to the helicopter power system: firstly, at least two cylinder bodies (24-4) are respectively and uniformly distributed on a shell (A) of the combined double-shaft output speed reducer by taking output shafts (Z16) and (Z12) as centers, a plunger (22-4) is connected in the cylinder body (24-4) in a sliding manner, a spring (23-4) is connected between the top in the cylinder body (24-4) and the outer end of the plunger (22-4), and the inner end of the plunger (22-4) is connected with the output shafts (Z16) and (Z12) of the combined double-shaft output speed reducer, namely: the disc cam (21-2) on the input shaft (Z19-2) of the radial plunger type load mechanism (J) is in sliding connection, N ascending and descending fillets formed by convex-concave bodies are uniformly distributed on the axial circumferential surface of the disc cam (21-2) in the radial direction, when the disc cam (21-2) rotates, a plunger (22-4) in sliding connection with the disc cam (21-2) is forced to move outwards along the longitudinal direction of a cylinder body (24-4) under the action of the ascending fillets, the plunger (22-4) moves outwards to press a compression spring (23-4) and a medium, the plunger (22-4) enables the plunger (22-4) to move back and suck the medium along with the descending fillets by the compression spring (23-4) after the ascending fillets reach the top points, and the spring (23-4) enables the plunger (22-4) to be always in sliding connection with the cam (21-2) in the reciprocating process, secondly, the top of a cylinder body (24-4) is connected with a medium pressure storage tank, a medium with certain pressure is arranged in the medium pressure storage tank, a control mechanism (25-4) amplifies a control valve hole after a plunger (22-4) reaches a top point, a medium back pressure plunger (22-4) with certain pressure presses the control valve to be closed after the back pressure plunger to follow a descending fillet of a cam (21-2) to descend to a low point, the plunger (22-4) starts to move outwards to compress the medium, the end part of the cylinder body (24-4) is connected with the medium inlet and outlet control mechanism (25-4), the control mechanism (25-4) controls an electromagnetic valve by the control mechanism according to the change of the rotating torque of a machine body (JT), the pressure in the cylinder body (24-4) is controlled by controlling the medium output flow in the cylinder body (24-4), so that the shell (A) of the combined double-shaft output speed reducer,

the disc brake load mechanism (D) is applied to the helicopter power system specifically: at least one set of fixed or floating brake calipers (32-4) is arranged on a combined double-shaft output speed reducer shell (A) by taking output shafts (16) and (12) as centers, wherein the output shafts (16) and (12) are as follows: the end part of an input shaft (Z26-2) of the disc type load mechanism (D) is connected with a brake disc (28-2) of the disc type brake load mechanism (D), the brake disc (28-2) is connected with a friction block (29-8), the friction block (29-8) is connected with a piston (30-8), the piston (30-8) is connected with a cylinder body (31-8), the cylinder body (31-8) is connected with a brake caliper (32-4), the cylinder body (31-8) is connected with a medium inlet and outlet hole (33-4), the medium inlet and outlet hole (33-4) is connected with a medium pressure control mechanism, the medium pressure control mechanism controls the medium pressure transmitted to the cylinder body (31-8) by a pressure source according to the change of the rotating torque of a machine body (JT), so that the piston (30-8) acts on the friction block (29-8) and is applied to the brake disc (28-2) The friction pressure of the combined double-shaft output speed reducer enables the shell (A) of the combined double-shaft output speed reducer to generate reaction torque,

the combined load mechanism (DJ) of the radial injection plug type mechanism and the disc type brake mechanism is applied to the helicopter power system in particular: at least two cylinder bodies (38-2) are respectively and uniformly distributed on the shell (A) of the combined double-shaft output speed reducer by taking the output shafts (16) and (12) as centers, and the output shafts (16) and (12) are as follows: the middle part of an input shaft (Z34-2) of the combined load mechanism (DJ) is connected with a bearing (41-2) connected with a shell (A) and a cam (35-2) of the combined load mechanism, the cam (35-2) is connected with a plunger (36-4), the plunger (36-4) is connected with a cylinder body (38-4), a spring (37-4) is connected between the cylinder body (38-4) and the plunger (36-4), the cylinder body (38-4) is connected with a medium inlet and outlet control mechanism (39-4), the end part of the input shaft (Z34-2) is connected with a brake disc (42-2), the brake disc (42-2) is connected with a friction block (43-8), the friction block (43-8) is connected with a piston (45-8), the piston (45-8) is connected with a cylinder body (44-8), the cylinder body (44-8) is connected with a fixed or floating brake caliper (46-4), the cylinder body (44-8) is connected with a medium inlet and outlet hole (47-4), the medium inlet and outlet hole (47-4) is connected with a medium pressure control mechanism, and the two mechanisms are controlled: one of the two can be fixedly arranged, the other can be controlled at any time along with the change of the torque of the machine body, the specific actuating mechanism adopts the traditional medium pressure technology, the control instruction is born by the attitude sensor, the computer and the instruction amplification component, and the manual control is used as a standby combined control mechanism.

Example 4:

a power system of a single-set rotor non-reaction torque tail rotor helicopter comprises: the helicopter is a helicopter in the prior art, the lower part of the main speed reducer (ZJ) is connected with a combined speed reducer (ZH1), the combined speed reducer (ZH1) is provided with one to five output shafts which rotate in the opposite directions of the rotating directions of the main speed reducer and the rotating direction of a rotor shaft and are different from the rotating direction of the rotor shaft, the output shaft of the combined speed reducer (ZH1) is connected with a load mechanism which is connected with a shell (A1), and the shell (A1) of the combined speed reducer is connected with a machine body (JT1) and forms relative balance torque with the machine body (JT 1); on the basis of the scheme, a power transmission system (WD) of a counter-torque tail rotor of the helicopter in the prior art is used for connecting a fixed thrust propeller or a tilting thrust propeller (TJ) on the tail of the helicopter.

Example 5:

the power system of a single-rotor-wing non-reactive-torque tail rotor helicopter described in embodiment 4, said combined speed reducer (ZH1) is composed of a planetary speed reduction unit and a parallel-shaft speed reduction unit, said one to five power output shafts are centered on a middle gear (56) in the parallel-shaft speed reduction unit, and teeth of the periphery thereof are uniformly distributed at 360 degrees and mesh with one to five output gears or output gear sets, said output gears or output gear sets are connected to an output shaft, and the rotation direction thereof is opposite to the rotation direction of the rotor shaft (YZ), and a combined two-shaft output speed reducer (ZH1) included in the combined speed reducer is taken as an example: the combined double-shaft output speed reducer (ZH1) and the main speed reducer (ZJ) have two connection modes, wherein the connection mode (L1) is as follows: the upper end of an input shaft (48) is connected with a main speed reducer shaft (Z0), the middle part of the input shaft is connected with a bearing (49) connected with a shell, the lower end of the input shaft is connected with a sun gear (50) of a combined speed reducer, the sun gear (50) is connected with at least three planetary gears (51-3) which are 120 degrees, the planetary gears (51-3) are connected with a planetary gear shaft (52-3) and a gear ring (53), the planetary gear shaft (53-3) is connected with a planet carrier (54), and the planet carrier (54): 1. when the combined type speed reducer (ZH1) is selected to output from a first shaft and a second shaft, the star frame (54) is connected with the middle shaft (55), 2, when the combined type speed reducer (ZH) is selected to output from a third shaft to a fifth shaft, the star frame (54) can be directly connected with the middle gear (56), the star frame (54) is connected with the middle shaft (55), two ends of the middle shaft (55) are connected with the bearings (57) and (58), the bearings (57) and (58) are connected with the shell (A1), the middle part of the middle shaft (55) is connected with the middle gear (56), the left side of the middle gear (56) is connected with the output gear (59), the output gear (59) is connected with the two ends of the output shaft (Z60) and the output shaft (Z60) and is connected with the bearings (61) and (62), the bearings (61) and (62) are connected with the shell (A1), the right side of the middle gear (56) is, (66) Bearings (65), (66) are connected to a housing (A1) in a manner (L2): when the connection mode (L2) is implemented, a speed reduction gear is respectively added between a middle gear (56) and a left output gear (59) and between the middle gear (56) and a right output gear (63) to ensure that the rotation direction of an output shaft is opposite to the rotation direction of a rotor shaft (YZ), the connection is connected with the lower part of a main speed reducer (ZJ), the upper part of the connection is connected with a combined speed reducer (ZH1) and a load mechanism thereof above the main speed reducer (ZJ), a sun gear (50) is sleeved on the rotor shaft (YZ), a star frame (54) and the middle gear (56) are connected with the rotor shaft (YZ) through a bearing by taking the rotor shaft (YZ) as the center, and the positions of other output gears are the same as the lower part of the connection.

Example 6:

the power system of a single-set rotor anti-torque tail rotor helicopter of examples 4 or 5, wherein the load mechanism comprises: the radial injection-plug type mechanism (JX) in the medium pressure technology, various clutches and couplers in the power transmission technology, the disc brake mechanism (ZD) in the coupling type coupling brake technology or one of the combined mechanisms (DJ1) of the two mechanisms are specifically applied,

the radial injection type load mechanism (JX) is applied to the reaction torque in the helicopter power system in particular: at least two cylinder bodies (72-4) are uniformly distributed on a shell (A1) of the combined double-shaft output speed reducer by taking an output shaft (Z60) and an output shaft (Z64) as the center, a plunger (70-4) is connected in the cylinder body (72-4) in a sliding manner, a spring (71-4) is connected between the inner top of the cylinder body (72-4) and the outer end of the plunger (70-4), and the inner end of the plunger (70-4) is connected with the output shafts (Z60) and (Z64) of the combined double-shaft output speed reducer, namely: the disc cam (69-2) on the input shaft (Z67-2) of the radial plunger type load mechanism is in sliding connection, N ascending and descending fillets formed by convex-concave bodies are uniformly distributed on the axial circumferential surface of the disc cam (69-2) in the radial direction, the disc cam (69-2) forces a plunger (70-4) in sliding connection with the disc cam (69-2) to move outwards along the longitudinal direction of a cylinder body (72-4) under the action of the ascending fillets when rotating, the plunger (70-4) moves a compression spring (71-4) and a medium outwards, the plunger (70-4) enables the plunger (70-4) to move back and suck the medium along with the descending fillets by the compressed spring (71-4) after the compression medium and the ascending fillets reach the top points, and the sliding connection state of the plunger (70-4) and the cam (69-2) is always kept by the spring (71-4) in the reciprocating process, secondly, the top of the cylinder body (72-4) is connected with a medium pressure storage tank, a medium with certain pressure is arranged in the medium pressure storage tank, the control mechanism (73-4) amplifies the control valve hole after the plunger (70-4) reaches the top point, the medium back pressure plunger (70-4) with certain pressure presses the control valve to be closed after the round angle descends to the low point along with the descending cam (69-2), the plunger (70-4) begins to move outwards to compress the medium, the end part of the cylinder body (72-4) is connected with the medium inlet and outlet control mechanism (73-4), the control mechanism (73-4) controls the electromagnetic valve by the control mechanism according to the change of the rotating torque of the machine body (JT), the pressure in the cylinder body (72-4) is controlled by controlling the medium output flow in the cylinder body (72-4), so that the combined double-shaft output speed reducer shell (A1) generates reaction torque.

The disc brake load mechanism (ZD) is applied to the helicopter power system specifically: at least one set of fixed or floating brake calipers (80-4) is respectively arranged on a combined double-shaft output speed reducer shell (A1) by taking an output shaft (Z60) and an output shaft (Z64) as a center, and the output shafts (Z60) and (Z64) of the double-shaft output type planetary speed reducer are as follows: the end part of an input shaft (74-2) of the disc brake load mechanism (ZD) is connected with a brake disc (76-2), the brake disc (76-2) is connected with a friction block (77-8), the friction block (77-8) is connected with a piston (78-8), the piston (78-8) is connected with a cylinder body (79-8), the cylinder body (79-8) is connected with a brake caliper (80-4), the cylinder body (79-8) is connected with a medium inlet and outlet hole (81-4), and the medium inlet and outlet hole (81-4) is connected with a medium pressure control mechanism, the medium pressure control mechanism controls the medium pressure transmitted to the cylinder body (79-8) by a pressure source according to the change of the rotating torque of a machine body (JT), so as to control the friction pressure applied to the brake disc (76-2) by the piston (78-8) acting on the friction block (77-8), so that the combined double-shaft output speed reducer shell (A1) generates reaction torque,

the combined loading mechanism (JD1) of the radial plug type mechanism and the disc type brake mechanism is applied to the helicopter power system: at least two cylinder bodies (87-2) are respectively and uniformly distributed on a combined double-shaft output speed reducer shell (A1) by taking output shafts (Z60) and (Z64) as centers, and the output shafts (Z60) and (Z64) of the combined double-shaft output speed reducer are as follows: an input shaft (Z82-2) of the combined load mechanism (JD1) is connected with a bearing (89-2) connected with a shell (A1) and a cam (84-2) of the combined load mechanism, the cam (84-2) is connected with an injection plug (85-4), the injection plug (85-4) is connected with a cylinder (87-4), a spring (86-4) is connected between the cylinder (87-4) and the injection plug (85-4), the cylinder (87-4) is connected with a medium inlet and outlet control mechanism (88-4), the end of the input shaft (Z82-2) is connected with a brake disc (90-2), the brake disc (90-2) is connected with a friction block (91-8), the friction block (91-8) is connected with a piston (93-8), and the piston (93-8) is connected with a cylinder (92-8), the cylinder (92-8) is connected with a fixed or floating brake caliper (94-4), the cylinder (92-8) is connected with a medium inlet and outlet hole (95-4), the medium inlet and outlet hole (95-4) is connected with a medium pressure control mechanism, and the two control mechanisms are controlled: one of the two combined control mechanisms can be fixedly arranged, the other one of the two combined control mechanisms can be controlled at any time along with the change of the torque of the machine body, the specific execution mechanism adopts the traditional medium pressure technology, a control instruction is born by an attitude sensing computer and an instruction amplification component, and manual control is used as a standby combined control mechanism.

Example 7:

the power system of a single-rotor-wing helicopter without a counter-torque tail rotor in embodiment 4, wherein a power transmission system (WD) of a counter-torque tail rotor of a helicopter in the prior art is connected with a fixed thrust propeller or a tilt thrust propeller (TJ) at a tail, the fixed flight thrust propeller is structurally composed of a conventional structure, the connection with a helicopter body (JT1) is a conventional connection manner, and the tilt thrust propeller (TJ) comprises: support (96), tilting arm (97), support (96) connect bearing (105-2), bearing (105-2) are connected and are connected tilting arm (97), tilting arm (97) connect bearing (98), (100), output shaft (99) is connected to bearing (98), (100), output shaft (99) front end connect thrust paddle (TJ), rear end connecting axle telescopic joint (101), ball cage or dual coupling (102) are connected to axle telescopic joint (101), ball cage or dual coupling (102) connect power input shaft (104), input shaft (104) connect bearing (103).

Example 8:

embodiment 7 a single unit rotor has a driving system of fixed or tilting flight thrust paddle helicopter, the tilting mechanism of tilting thrust paddle is cylinder and plunger type structure in hydraulic technology, the motor and gear type structure constitute, through connecting cylinder with supporting seat plunger and connecting the tilting arm, the tilting arm is realized tilting less than 100 degrees about with contracting of plunger, supporting seat connects the motor, the motor connects the gear, the gear connection tilting gear, tilting gear connects the tilting arm's interlock realizes tilting less than 100 degrees about the tilting arm does.