Tailroom gas vane transmission system and control method thereof

Abstract

The invention discloses a stern room gas vane transmission system and a control method thereof, and relates to the technical field of aircraft flight, and the gas vane transmission system comprises an air vane and a gas vane which are arranged on a cabin section shell; an air rudder shaft of the air rudder penetrates through one end of the cabin section shell and is connected with a driving end of the steering engine; the air rudder is in transmission connection with the gas rudder through a transmission assembly; the gas vane is connected with the bottom of the cabin section shell through at least two separation pieces; the separating part has a first working state and a second working state; in the first working state, the separation piece keeps the connection between the gas vane and the cabin section shell; and in the second working state, the separation piece cuts off the connection between the gas vane and the cabin section shell, so that the gas vane is separated from the cabin section shell. The system can abandon the unnecessary weight of the gas vane for the aircraft after the solid engine of the aircraft finishes working, so that the range or other flight indexes of the aircraft are improved.

Description

Technical Field

[0001] The present disclosure generally relates to the field of aircraft flight technology, and in particular to a tail compartment gas rudder transmission system and a control method thereof. Background Art

[0002] With the development of science and technology, various aircrafts emerge in an endless stream. As a type of aircraft, rockets are particularly important for attitude control during flight, which is related to whether the rocket can fly according to the predetermined route. Air rudders and gas rudders are mainly used on controlled rockets. Compared with fixed wings, the cooperation between air rudders and gas rudders is more efficient in maintaining the stability of the rocket's attitude.

[0003] In the prior art, during the working period of the aircraft's solid engine, the aircraft's attitude is mainly adjusted by the gas rudder. After the solid engine stops working, the aircraft obtains a certain flight speed, and the aircraft's attitude is switched to the air rudder for adjustment. At this time, although the gas rudder still rotates together with the air rudder, the gas rudder no longer exerts control on the aircraft. This makes the gas rudder's own weight at this time become an invalid weight or additional weight that affects the aircraft's flight indicators, thereby reducing the aircraft's range or other flight indicators. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a tail compartment gas rudder transmission system and a control method thereof.

[0005] In a first aspect, the present application provides a tail cabin gas rudder transmission system, the gas rudder transmission system comprising: an air rudder and a gas rudder arranged on a cabin shell; The air rudder shaft of the air rudder passes through one end of the cabin shell and is connected to the driving end of the steering gear; the air rudder is connected to the gas rudder through a transmission assembly; The gas rudder is connected to the bottom of the compartment shell through at least two separation parts; the separation parts have a first working state and a second working state; in the first working state, the separation parts maintain the connection between the gas rudder and the compartment shell so that the air rudder transmits power to the gas rudder; in the second working state, the separation parts cut off the connection between the gas rudder and the compartment shell so that the gas rudder is separated from the compartment shell.

[0006] According to the technical solution provided in the present application, the transmission assembly includes: a first transmission part and a second transmission part that cooperate with each other; The first transmission part is connected to the air rudder shaft of the air rudder, and the second transmission part is transmission-connected to the gas rudder; the servo drives the air rudder to rotate, thereby driving the first transmission part and the second transmission part to drive the gas rudder to rotate.

[0007] According to the technical solution provided in the present application, the first transmission part includes: a first bearing arranged at both ends of the air rudder shaft and a first gear arranged in the middle of the air rudder shaft; the first bearing is used to support the air rudder shaft to rotate in the cabin shell.

[0008] According to the technical solution provided by the present application, the second transmission part includes: an intermediate shaft, the intermediate shaft is connected to the compartment housing through a second bearing; a second gear is fixedly connected to the intermediate shaft, and the second gear is meshed with the first gear; The second gear is a gear sleeve structure, and the gear sleeve is also provided with a rocker arm, and the rocker arm extends in a direction close to the gas rudder; the rocker arm is movably sleeved with the gas rudder.

[0009] According to the technical solution provided in the present application, the gas rudder has a gas rudder shaft, and the gas rudder shaft is connected to the rocker arm transmission through a rotating connection part, and the rotating connection part is used to receive the driving force transmitted by the transmission assembly to rotate the gas rudder shaft.

[0010] According to the technical solution provided in the present application, the gas rudder is connected to the bottom of the compartment shell through the gas rudder mounting base plate; the separation member is arranged through the gas rudder mounting base plate and the compartment shell; The rotating connection part comprises: a bearing support is arranged on a side of the gas rudder mounting base plate away from the compartment shell, and a bearing structure for supporting the rotation of the gas rudder shaft is arranged in the bearing support; the bearing structure comprises: a bearing retaining ring, a third bearing and a bearing end cover; A shift fork, one end of which is connected to the end of the gas rudder shaft that passes through the bearing structure through a shift fork retaining ring, and the other end of which passes through the gas rudder mounting base plate and is movably sleeved with the rocker arm.

[0011] According to the technical solution provided in the present application, a gas rudder heat protection plate is provided at the bottom of the gas rudder close to the gas rudder shaft.

[0012] According to the technical solution provided in the present application, a plurality of receiving grooves are provided on the bottom of the compartment shell and the gas rudder mounting base plate corresponding to each other, and the plurality of receiving grooves are evenly distributed on both sides of the air rudder and the gas rudder; every two corresponding receiving grooves constitute a receiving space, and an elastic element is arranged in the receiving space.

[0013] In a second aspect, the present application provides a control method for a tail compartment gas rudder transmission system, which is applied to the above-mentioned tail compartment gas rudder transmission system, wherein the separation member in the transmission system is a separation bolt; the control method comprises: During the engine operation period, receiving a first control instruction, wherein the first control instruction is used to adjust the rotation angle of the gas rudder surface; Based on the first control instruction, the air rudder is driven by the steering gear to drive the gas rudder to rotate through the transmission assembly, so that the rudder surface of the gas rudder rotates, thereby adjusting the direction and magnitude of the lateral force generated by the engine gas flow on the rudder surface of the gas rudder; When the engine operation ends, the working state of the separation component is switched from the first working state to the second working state, and under the push of the elastic element, the gas rudder mounting base plate and the gas rudder thereon are separated from the cabin shell together.

[0014] To summarize, the present technical solution specifically discloses a tail cabin gas rudder transmission system and a control method thereof, wherein the gas rudder transmission system comprises: an air rudder and a gas rudder arranged on the cabin shell; the air rudder shaft of the air rudder passes through one end of the cabin shell and is connected to the driving end of the servo; the air rudder and the gas rudder are connected through a transmission assembly; the gas rudder is connected to the bottom of the cabin shell through at least two separation parts; the separation parts have a first working state and a second working state; in the first working state, the separation part maintains the connection between the gas rudder and the cabin shell so that the air rudder transmits power to the gas rudder; in the second working state, the separation part cuts off the connection between the gas rudder and the cabin shell so that the gas rudder is separated from the cabin shell.

[0015] When the solid engine of the current aircraft is finished working, the attitude of the aircraft is switched to the air rudder for adjustment. At this time, although the gas rudder still rotates together with the air rudder, it brings invalid weight or extra weight to the aircraft, thereby affecting the range or other flight indicators of the aircraft. In the present application, the air rudder and the gas rudder are connected through a transmission assembly, so that the driving force of the servo can be transmitted to the gas rudder through the air rudder and the transmission assembly slidably connected to the gas rudder, thereby adjusting the attitude of the aircraft; at the same time, the gas rudder is connected to the bottom of the cabin shell through at least two separation parts. After the separation part is switched from the first working state to the second working state, the separation part can cut off the connection between the gas rudder and the cabin shell, so that the gas rudder and the cabin shell are separated, which is equivalent to discarding unnecessary weight for the aircraft, and can also reduce the flight resistance of the aircraft, thereby improving the range or other flight indicators of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings: Figure 1 It is a front view of a tail compartment gas rudder transmission system.

[0017] Figure 2It is a cross-sectional view of a tail compartment gas rudder transmission system in the AA direction.

[0018] Figure 3 It is a cross-sectional view of a tail compartment gas rudder transmission system in the BB direction.

[0019] Figure 4 It is a cross-sectional view of a tail compartment gas rudder transmission system in the DD direction.

[0020] Figure 5 It is a cross-sectional view of a tail compartment gas rudder transmission system in the CC direction.

[0021] Figure 6 The present invention is a flow chart of a control method of a tail compartment gas rudder transmission system.

[0022] Numbers in the figure: 1, cabin shell; 2, air rudder; 21, air rudder shaft; 3, gas rudder; 31, gas rudder shaft; 4, steering gear; 5, separation part; 6, first bearing; 7, first gear; 8, intermediate shaft; 9, second bearing; 10, second gear; 11, rocker arm; 12, gas rudder mounting base plate; 13, bearing support; 14, bearing retaining ring; 15, third bearing; 16, bearing end cover; 17, shift fork; 18, shift fork retaining ring; 19, gas rudder heat shield; 20, receiving groove; 22, elastic element; 23, first pin; 24, second pin; 25, third pin. DETAILED DESCRIPTION

[0023] The present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant inventions, rather than to limit the inventions. It should also be noted that, for ease of description, only the parts related to the invention are shown in the accompanying drawings.

[0024] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0025] Example 1 In order to make the technical solution of the embodiment of the present application clearer and easier to understand, the application background of the embodiment of the present application is introduced below.

[0026] The gas rudder system is a key component used to control the flight direction of an aircraft, especially an aircraft powered by a solid rocket engine. The gas rudder is usually installed at the nozzle outlet of a solid rocket engine, and uses the reaction force generated by the gas generated when the engine is working and flows through the gas rudder surface to control the flight attitude and direction of the aircraft. When the gas rudder surface is not deflected, the airflow on both sides passes through it symmetrically, and the forces generated on both sides of the gas rudder surface are equal in magnitude and opposite in direction, canceling each other out. When the gas rudder surface is deflected, the airflow flowing through its two sides is asymmetrical, which will generate a lateral force on the gas rudder surface. By adjusting the deflection angle of the gas rudder surface, the direction and magnitude of the lateral force can be adjusted, thereby changing the attitude and trajectory of the aircraft.

[0027] The existing gas rudder system generally consists of: air rudder surface (including rudder shaft), cabin shell, electric rudder, air rudder crank, adjusting connecting rod, gas rudder crank and gas rudder surface (including rudder shaft), etc. The electric rudder drives the air rudder crank to rotate, so that the air rudder rotates with the air rudder crank. At the same time, the air rudder crank drives the gas rudder crank to rotate through the adjusting connecting rod, thereby driving the gas rudder shaft and gas rudder surface to rotate together.

[0028] However, in the actual movement of the aircraft, during the working period of the aircraft's solid engine, the aircraft's attitude is mainly adjusted by the gas rudder; after the solid engine finishes working, the aircraft obtains a certain flight speed, and the aircraft's attitude is switched to the air rudder for adjustment. At this time, although the gas rudder still rotates together with the air rudder, the gas rudder no longer exerts control over the aircraft. At this time, the gas rudder's own weight has become an invalid weight or additional weight that affects the aircraft's flight indicators, which will reduce the aircraft's range or other flight indicators.

[0029] In view of this, please refer to Figure 1 , Figure 2 and Figure 5 The embodiment shown in the figure shows a front view of a tail cabin gas rudder transmission system and a cross-sectional view thereof in the AA direction and a cross-sectional view thereof in the CC direction. The gas rudder transmission system comprises: an air rudder 2 and a gas rudder 3 arranged on a cabin shell 1; The air rudder shaft 21 of the air rudder 2 passes through one end of the cabin shell 1 and is connected to the driving end of the steering gear 4; the air rudder 2 is connected to the gas rudder 3 through a transmission assembly; The gas rudder 3 is connected to the bottom of the cabin shell 1 through at least two separators 5; the separator 5 has a first working state and a second working state; in the first working state, the separator 5 maintains the connection between the gas rudder 3 and the cabin shell 1 so that the air rudder 2 transmits power to the gas rudder 3; in the second working state, the separator 5 cuts off the connection between the gas rudder 3 and the cabin shell 1 so that the gas rudder 3 is separated from the cabin shell 1.

[0030] In the embodiment of the present application, the gas rudder transmission system includes an air rudder 2 and a gas rudder 3, and both are components for controlling the attitude and direction of the aircraft. Among them, the air rudder 2 generates control force by utilizing the air flow around the aircraft. When the surface shape and angle of the air rudder change, it will change the airflow around the aircraft, thereby generating additional force or torque to help the aircraft change direction or adjust its attitude; while the gas rudder 3 is a device that generates control force by utilizing the ejected gas flow. It is usually set near the engine nozzle of a rocket or missile. When the control surface of the gas rudder 3 changes, it will change the direction and speed of the gas flow, thereby generating a reaction force to help the aircraft change its attitude and direction. The reaction force generated by the gas generated when the engine is working and flowing through the control surface of the gas rudder is used to control the flight attitude and direction of the aircraft.

[0031] Based on the above description, it can be known that the air rudder 2 and the gas rudder 3 need to help the aircraft change direction or adjust its attitude according to its actual flight state, so the air rudder 2 and the gas rudder 3 need to adjust the direction and magnitude of the lateral force generated by the engine gas flow on the gas rudder surface by adjusting the rotation angle of their own rudder surfaces; in the embodiment of the present application, the air rudder shaft 21 of the air rudder 2 is connected to the driving end of the servo 4, so under the drive of the servo 4, the air rudder shaft 21 can drive the rudder surface of the air rudder 2 to rotate to a corresponding angle; in the stage where the gas rudder 3 is needed to control the attitude of the aircraft, since the air rudder 2 is connected to the gas rudder 3 through a transmission assembly, the rotation control required by the gas rudder 3 can also be used by the servo 4 as a power source, and the air rudder 2 is transmitted to the gas rudder 3 through the transmission assembly.

[0032] Furthermore, in order to prevent the gas rudder 2 from serving as invalid weight or additional weight of the aircraft after the engine stops working, the embodiment of the present application also includes at least two separation components 5. The separation components 5 may be separation bolts, which can provide a connecting force and be unlocked in time under control to assist the gas rudder 3 in separating from the cabin shell 1. Specifically, the gas rudder 3 is arranged at the bottom of the cabin shell 1, and the gas rudder shaft 31 and the air rudder shaft 21 of the gas rudder 3 are in parallel. The transmission assembly is arranged between the gas rudder shaft 31 and the air rudder shaft 21 to transmit power. Since the gas rudder 3 is essentially slidably connected to the transmission assembly, the unlocking of the separation component 5 will not be affected when the separation component 5 is in the second working state.

[0033] In a preferred embodiment, if Figure 2 As shown, the transmission assembly includes: a first transmission part and a second transmission part that cooperate with each other; The first transmission part is connected to the air rudder shaft 21 of the air rudder 2, and the second transmission part is connected to the gas rudder 3; the steering gear 4 drives the air rudder 1 to rotate, thereby driving the first transmission part and the second transmission part to drive the gas rudder 3 to rotate.

[0034] Specifically, the first transmission part and the second transmission part cooperate with each other to realize the transmission of the air rudder 2 and the gas rudder 3, wherein the first transmission part is responsible for connecting with the air rudder shaft 21 of the air rudder 2, and the second transmission part is slidingly connected with the gas rudder 3 along a first direction, where the first direction is the axial direction perpendicular to the air rudder shaft 21, so the driving force of the air rudder shaft 21 in its axial direction can be completely transmitted when the second transmission part and the gas rudder 3 are in a sliding connection. At this time, the separator 5 has not been unlocked, and the gas rudder 3 and the compartment shell 1 have sufficient supporting force in the first direction.

[0035] In a preferred embodiment, if Figure 2 As shown, the first transmission part includes: first bearings 6 arranged at both ends of the air rudder shaft 21 and a first gear 7 arranged in the middle of the air rudder shaft 21; the first bearing 6 is used to support the air rudder shaft 21 to rotate in the cabin shell 1.

[0036] Specifically, a shell or a connecting structure such as a structural plate for fixing the corresponding parts of the air rudder 2 is formed inside the cabin shell 1 to meet the installation requirements of the air rudder 2. Two mounting positions of the first bearings 6 are provided at the connecting structure. After passing through the cabin shell 1, the air rudder shaft 21 is rotatably sleeved inside the two first bearings 6. A first gear 7 is also fixed to the outside of the air rudder shaft 21 through a first pin 23 for transmitting the driving force of the servo 4 to the second transmission part.

[0037] Furthermore, if Figure 2 As shown, the second transmission part includes: an intermediate shaft 8, which is connected to the cabin shell 1 through a second bearing 9; a second gear 10 is fixedly connected to the intermediate shaft 8, and the second gear 10 is meshed with the first gear 7; wherein the second gear 10 is a gear sleeve structure, and the gear sleeve also has a rocker arm 11, and the rocker arm 11 extends in a direction close to the gas rudder 3; the rocker arm 11 is movably sleeved with the gas rudder 3.

[0038] The intermediate shaft 8 is arranged at the connection structure through two second bearings 9 located at the ends. The second bearings 9 are used to support the rotation of the intermediate shaft 8. The intermediate shaft 8 is fixed with a second gear 10 through a second pin 24. The second gear 10 is meshed with the first gear 7. Therefore, when the first gear 7 rotates, the second gear 10 and the intermediate shaft 8 also rotate accordingly; see Figure 2-Figure 4 The second gear 10 is a gear sleeve structure, that is, a gear structure is arranged on the outside of a sleeve structure, and a rocker arm 11 extending toward the direction close to the gas rudder 3 is also arranged on the sleeve structure, and the rocker arm 11 is used to transmit driving force to the gas rudder 3.

[0039] In a preferred embodiment, if Figure 2As shown, the gas rudder 3 has a gas rudder shaft 31, and the gas rudder shaft 31 is transmission-connected to the rocker arm 11 via a rotating connection portion, and the rotating connection portion is used to receive the driving force transmitted by the transmission assembly to rotate the gas rudder shaft 31.

[0040] Specifically, the gas rudder 3 also has a gas rudder shaft 31, and the gas rudder shaft 31 is slidably connected with the rocker arm 11 through a rotating connection portion, so that the gas rudder 3 can be driven to rotate through the rotating connection portion when the rocker arm 11 rotates.

[0041] In order not to hinder the rotation of the gas rudder 3, the gas rudder 3 is connected to the bottom of the cabin shell 1 through the gas rudder mounting base plate 12; therefore, the separator 5 is arranged through the gas rudder mounting base plate 12 and the cabin shell 1, so that the gas rudder shaft 31 can rotate relative to the gas rudder mounting base plate 12; in order to ensure the stability of subsequent separation, in the embodiment of the present application, the gas rudder mounting base plate 12 is a plate with a large area, and the number of the separators 5 is at least two, and the two separators 5 can be symmetrically arranged on both sides of the air rudder 2 and the gas rudder 3.

[0042] Furthermore, if Figure 2 As shown, the rotating connection part includes: a bearing support 13 is arranged on the side of the gas rudder mounting base plate 12 away from the cabin shell 1, and a bearing structure for supporting the rotation of the gas rudder shaft 31 is arranged in the bearing support 13; the bearing structure includes: a bearing retaining ring 14, a third bearing 15 and a bearing end cover 16; The shift fork 17 has one end connected to the end of the gas rudder shaft 31 penetrating the bearing structure through a shift fork retaining ring 18 , and the other end penetrates the gas rudder mounting bottom plate 12 and is movably sleeved with the rocker arm 11 .

[0043] The bearing support 13 is a conventional mounting seat structure for installing the gas rudder 3. In order to ensure the stable rotation of the gas rudder 3, a third bearing 15 for supporting the rotation of the gas rudder shaft 31, a bearing retaining ring 14 fixed to the circumference of the gas rudder shaft 31 by a third pin 25, and a bearing end cover 16 arranged at the bottom of the bearing support 13 are arranged in the bearing support 13. The gas rudder shaft 31 passes through the bearing end cover 16 and is connected with a shift fork 17. The shift fork 12 is pressed and installed on the gas rudder shaft 31 by a shift fork retaining ring 18, and is used to drive the gas rudder shaft 31 to rotate.

[0044] The fork 12 is provided with a connection hole for cooperating with the rocker arm 11. The end of the rocker arm 11 away from the second gear 10 is provided with a protrusion matching with the connection hole. The protrusion is slidably located in the connection hole. Figure 1 The connection state shown in the figure drives the fork 17 to swing through the rocker arm 11, so as to drive the gas rudder shaft and the gas rudder surface to rotate.

[0045] Based on the above description, it can be seen that in the embodiment of the present application, there is the following transmission relationship: The rotation process of the air rudder 2 is as follows: the air rudder shaft 21 is directly driven by the steering gear 4 to rotate; The rotation process of the gas rudder 3 is as follows: the air rudder shaft 21 is driven to rotate by the servo engine 2, and the air rudder shaft 21 simultaneously drives the first gear 7 fixed thereto to rotate. Under the rotation of the first gear 7, the second gear 10 is driven to rotate, and drives the rocker arm 11 thereon to swing a corresponding angle. Since the rocker arm 11 and the shift fork 12 are arranged in coordination with each other, the shift fork 12 will also swing a corresponding angle at this time, and the end of the shift fork 12 is fastened to the end of the gas rudder shaft 31, thereby completing the operation of driving the gas rudder shaft 31 to rotate.

[0046] In a preferred embodiment, if Figure 4 As shown, a gas rudder heat shield 19 is provided at the bottom of the gas rudder 3 near the gas rudder shaft 31 .

[0047] Specifically, as can be seen from the above introduction to the gas rudder 3, the gas rudder 3 is a device that utilizes the ejected gas flow to generate control force, and is usually arranged near the engine nozzle of a rocket or missile. Therefore, a gas rudder heat protection plate 19 is also provided at the bottom of the gas rudder 3 to increase the life of the gas rudder 3 and ensure that the gas rudder 3 can work stably within the time before the engine stops working.

[0048] In a preferred embodiment, if Figure 4 As shown, a plurality of receiving grooves 20 corresponding to each other are provided on the bottom of the cabin shell 1 and the gas rudder mounting base plate 12, and the plurality of receiving grooves 20 are evenly distributed on both sides of the air rudder 2 and the gas rudder 3; every two corresponding receiving grooves 20 constitute a receiving space, and an elastic element 22 is provided in the receiving space.

[0049] Specifically, a plurality of corresponding receiving grooves 20 are provided between the bottom of the compartment shell 1 and the gas rudder mounting base plate 12, and the openings of two corresponding receiving grooves 20 are opposite to each other, thereby forming a receiving space, in which an elastic element 22 is placed. The type of the elastic element 22 is, for example, a spring. The spring needs to be in a compressed state, and the compression direction is the separation direction of the gas rudder 3 from the compartment shell 1, thereby providing an initial driving force for the bottom of the compartment shell 1 and the gas rudder mounting base plate 12, and ensuring the rapid and stable separation of the two.

[0050] Combination Figure 1-Figure 5 Based on the above content and the aforementioned description of the rotation relationship, it can be seen that the embodiment of the present application proposes a tail cabin gas rudder transmission system, and its specific working principle is as follows: During the working stage of the solid engine of the aircraft, the separation member 5 is in the first working state, that is, the unlocked state, the gas rudder 3 is kept connected to the cabin shell 1, and the steering gear 4 drives the gas rudder 3 to rotate through the air rudder 2 and the transmission assembly, and adjusts the rotation angle of the gas rudder surface, thereby adjusting the direction and magnitude of the lateral force generated by the engine gas flow on the gas rudder surface, thereby changing the attitude and trajectory of the aircraft; After the solid engine has finished working, the gas rudder 3 no longer provides control force for the aircraft. At this time, the separation piece 2 is unlocked to put it in the second working state, the connection between the gas rudder 3 and the cabin shell 1 is cut off, and the gas rudder mounting base plate 12 is disconnected from the cabin shell 1. Under the pushing force of the elastic element 22, the gas rudder mounting base plate 12 and the gas rudder 3 are quickly separated from the cabin shell 1.

[0051] Example 2 See also Figure 6 Based on a tail compartment gas rudder transmission system provided in Example 1, the present application embodiment provides a control method for the tail compartment gas rudder transmission system, wherein the separation member 5 in the transmission system is a separation bolt, and the control method includes: S100, receiving a first control instruction during the engine operation period, the first control instruction being used to adjust the rotation angle of the control surface of the gas rudder 3; S200, based on the first control instruction, the air rudder is driven by the servo 4 to drive the gas rudder 3 to rotate through the transmission assembly, so that the rudder surface of the gas rudder 3 rotates, thereby adjusting the direction and magnitude of the lateral force generated by the engine gas flow on the rudder surface of the gas rudder 3; S300, when the engine operation ends, the working state of the separation component 5 is switched from the first working state to the second working state, and under the push of the elastic element 21, the gas fin mounting base plate 12 and the gas fin 3 thereon are separated from the cabin shell 1 together.

[0052] Specifically, during the engine operating time period, the first control instruction can be issued by the aircraft's telemetry main system. The first control instruction needs to be determined in combination with the direction and magnitude of the lateral force generated by the engine gas flow currently acting on the aircraft body on the gas rudder surface. It is calculated and analyzed within the telemetry main system and is not specifically limited here.

[0053] Furthermore, the first control instruction includes at least the specific numerical value of the attitude angle that the aircraft needs to adjust, and the attitude angle includes at least the pitch angle, the roll angle and the yaw angle; after receiving the first control instruction, it is also necessary to parse it into an electrical signal that can be rotated by the rotatable servo 4, and the servo 4 responds and drives the gas rudder 3 to rotate according to the electrical signal obtained by parsing the first control instruction.

[0054] After the solid engine is finished working, the aircraft obtains a certain flight speed, and the aircraft attitude is switched to the air rudder for adjustment. At this time, although the gas rudder still rotates together with the air rudder, the gas rudder 3 no longer exerts control force on the aircraft. This makes the weight of the gas rudder 3 itself become an invalid weight or additional weight that affects the flight indicators of the aircraft, which will further reduce the range or other flight indicators of the aircraft. Therefore, when the engine operation ends, the telemetry main system sends a control command to unlock the separation component 5. At this time, the separation component 5 responds to the control command to unlock (the working state of the separation component 5 is switched from the first working state to the second working state), and the connection between the gas rudder 3 and the cabin shell 1 is cut off. Under the cooperation and push of the elastic element 21, the gas rudder mounting base 12 and the gas rudder 3 thereon are separated from the cabin shell 1 together; subsequently, the telemetry main system only needs to send an attitude adjustment command to the air rudder 2 to ensure the attitude of the aircraft.

[0055] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. A tail compartment gas rudder transmission system, characterized in that: The gas rudder transmission system comprises: an air rudder (2) and a gas rudder (3) arranged on the cabin shell (1); An air rudder shaft (21) of the air rudder (2) passes through one end of the cabin shell (1) and is connected to a driving end of a steering gear (4); the air rudder (2) is connected to the gas rudder (3) through a transmission assembly; The gas rudder (3) is connected to the bottom of the cabin shell (1) via at least two separation components (5); the separation components (5) have a first working state and a second working state; in the first working state, the separation components (5) maintain the connection between the gas rudder (3) and the cabin shell (1), so that the air rudder (2) transmits power to the gas rudder (3); in the second working state, the separation components (5) cut off the connection between the gas rudder (3) and the cabin shell (1), so that the gas rudder (3) is separated from the cabin shell (1).

2. A tail compartment gas rudder transmission system according to claim 1, characterized in that: The transmission assembly comprises: a first transmission part and a second transmission part that cooperate with each other; The first transmission part is connected to the air rudder shaft (21) of the air rudder (2), and the second transmission part is in transmission connection with the gas rudder (3); the steering gear (4) drives the air rudder (1) to rotate, thereby driving the first transmission part and the second transmission part to drive the gas rudder (3) to rotate.

3. A tail compartment gas rudder transmission system according to claim 2, characterized in that: The first transmission part comprises: first bearings (6) arranged at both ends of the air rudder shaft (21) and a first gear (7) arranged in the middle of the air rudder shaft (21); the first bearing (6) is used to support the air rudder shaft (21) to rotate in the compartment shell (1).

4. A tail compartment gas rudder transmission system according to claim 3, characterized in that: The second transmission part comprises: an intermediate shaft (8), the intermediate shaft (8) being connected to the compartment shell (1) via a second bearing (9); a second gear (10) being fixedly connected to the intermediate shaft (8), the second gear (10) being meshed with the first gear (7); The second gear (10) is a gear sleeve structure, the gear sleeve also has a rocker arm (11), the rocker arm (11) extends in a direction close to the gas rudder (3); the rocker arm (11) is movably sleeved with the gas rudder (3).

5. A tail compartment gas rudder transmission system according to claim 4, characterized in that: The gas rudder (3) has a gas rudder shaft (31), and the gas rudder shaft (31) is transmission-connected to the rocker arm (11) via a rotating connection portion, and the rotating connection portion is used to receive a driving force transmitted by the transmission assembly to rotate the gas rudder shaft (31).

6. A tail compartment gas rudder transmission system according to claim 5, characterized in that: The gas rudder (3) is connected to the bottom of the compartment shell (1) via a gas rudder mounting base plate (12); the separation component (5) is arranged through the gas rudder mounting base plate (12) and the compartment shell (1); The rotating connection portion comprises: a bearing support (13) arranged on a side of the gas rudder mounting base plate (12) away from the compartment shell (1), a bearing structure for supporting the rotation of the gas rudder shaft (31) being arranged in the bearing support (13); the bearing structure comprises: a bearing retaining ring (14), a third bearing (15) and a bearing end cover (16); A shift fork (17), one end of the shift fork (17) being connected to the end of a gas rudder shaft (31) penetrating the bearing structure via a shift fork retaining ring (18), and the other end of the shift fork penetrating the gas rudder mounting base plate (12) being movably sleeved with the rocker arm (11).

7. A tail compartment gas rudder transmission system according to claim 6, characterized in that: A gas rudder heat protection plate (19) is provided at the bottom of the gas rudder (3) close to the gas rudder shaft (31).

8. The tail compartment gas rudder transmission system according to claim 6, characterized in that: The bottom of the cabin shell (1) and the gas vane mounting bottom plate (12) are provided with a plurality of receiving grooves (20) arranged corresponding to each other, and the plurality of receiving grooves (20) are evenly distributed on both sides of the air vane (2) and the gas vane (3); every two corresponding receiving grooves (20) form a receiving space, and an elastic element (22) is arranged in the receiving space.

9. A control method for a tail compartment gas rudder transmission system, characterized in that: Applicable to the tail compartment gas rudder transmission system according to any one of claims 1 to 8 above, wherein the separation member (5) in the transmission system is a separation bolt; the control method comprises: During the engine operation period, a first control instruction is received, the first control instruction being used to adjust the rotation angle of the control surface of the gas rudder (3); Based on the first control instruction, the steering gear (4) drives the air rudder to rotate the gas rudder (3) through the transmission assembly, so as to rotate the rudder surface of the gas rudder (3), thereby adjusting the direction and magnitude of the lateral force generated by the engine gas flow on the rudder surface of the gas rudder (3); When the engine operation ends, the working state of the separation component (5) is switched from the first working state to the second working state, and the gas vane mounting base plate (12) and the gas vane (3) thereon are separated from the cabin shell (1) together under the push of the elastic element (21).

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