Collector ring capable of deicing during rotation of rotor wing of rotorcraft
By designing a current collecting ring on the rotorcraft, using signals and electrical power to transmit to the propeller assembly, blade heating is achieved, which solves the problem of impact on the flight performance of the rotorcraft under icy conditions, and improves maintenance and safety.
Patent Information
- Application Number
- CN202420512167.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-03-15
- Publication Date
- 2024-12-24
- Estimated Expiration
- 2034-03-15
AI Technical Summary
Under frozen meteorological conditions, rotor blades are prone to freezing, resulting in flight performance that may even be out of control or damaged. The existing anti-icing measures are complex and maintenance costs are high.
Design a current collecting ring that can deicine when rotor rotor rotates, including rotors, base housing, brush boxes, conductive support, brushes and conductive rings, which can transmit signals and electrical power to the propeller assembly to realize the blades Heating and signal input and output, preventing deicing.
It improves maintenance, reduces maintenance costs, and enhances the service life, reliability and safety of rotorcraft. It is suitable for rotorcraft with various structurally defined rotorcraft and can be installed without disassembling the engine and propeller.
Smart Images
Figure CN222224430U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of collector rings, in particular to a collector ring capable of realizing deicing when a rotor of a rotorcraft rotates. Background Art
[0002] When a rotorcraft flies under icing weather conditions, supercooled water droplets in the atmosphere will quickly gather on the leading edge of the high-speed rotating rotor blades and condense into ice. The icing of the rotor blades will bring some serious effects, such as changing the aerodynamic shape of the rotor blades, affecting the flight performance of the rotorcraft, and in serious cases, easily causing the aircraft to lose control and stall, or even crash. Some ice will fall off the high-speed rotating rotor blades, damage other parts of the rotorcraft, and affect the flight safety of the rotorcraft.
[0003] Therefore, rotorcraft need to be treated with anti-icing and de-icing to prevent supercooled water droplets from condensing into ice on the rotor blades, or to allow a certain thickness of ice to form during the de-icing process before de-icing. Utility Model Content
[0004] In order to solve the above technical problems, the utility model proposes a collector ring capable of deicing a rotorcraft rotor when it is rotating, and is used for deicing a rotorcraft rotor when it is rotating.
[0005] The utility model adopts the following technical solutions:
[0006] A collector ring capable of realizing deicing when a rotor of a rotary-wing aircraft rotates, comprising: a rotor, a base cover, a brush box, N conductive supports of different lengths, N brushes and N conductive rings; N is the number of propeller blades; the rotor is installed in the base cover; the base cover is detachably installed on a power assembly; the brush box is installed on the base cover; the rotor is fixed to the propeller assembly through a rotor support;
[0007] The conductive support is electrically connected to the conductive ring through a conductive pin, a rotor end cable is provided on the conductive support, the rotor end cable is fixed on the conductive support, and the conductive pin limits the conductive ring;
[0008] The brush box is provided with a cable cavity and a plurality of brush cavities; each of the brush cavities accommodates one brush, and one end of the brush is pressed into the brush cavity by the brush clamping spring; one end of the brush is connected to a fixed-end cable, and the fixed-end cable passes through the cable cavity; the other end of the brush has a conductive ring cavity, and the conductive ring cavity cooperates with the outer wall of the conductive ring; the brush is pressed against the outer wall of the conductive ring by the brush clamping spring; the inner side surface of the conductive support cooperates with the propeller shaft on the propeller assembly; the brush transmits signals and electrical power to the conductive support through the conductive pin.
[0009] The rotor includes a first rotor and a second rotor that are detachably connected.
[0010] Each of the conductive rings comprises two semicircular conductive rings with the same structure, and the two semicircular conductive rings are detachably connected.
[0011] The semicircular conductive ring is provided with a connecting ear piece, and the connecting ear piece is connected by a detachable conductive ring fastener.
[0012] The base outer cover comprises a first base outer cover and a second base outer cover which have the same structure and are detachably connected.
[0013] The first base housing and the second base housing are mounted on the power assembly via base fasteners.
[0014] Conductive support grooves are provided on the inner walls of the first rotor and the second rotor, and the conductive support is installed in the conductive support grooves.
[0015] The rotor end cable is fixed on the conductive support by a conductive support fastener.
[0016] The rotor and the conductive support are detachably connected via a conductive support fastener.
[0017] The outer walls of the first rotor and the second rotor are both provided with grooves, the conductive rings are installed in the grooves, and the grooves are matched with the outer walls of the conductive rings.
[0018] The utility model provides a collector ring that can realize deicing when the rotor of a rotorcraft rotates, comprising a rotor support, a rotor, a base cover, a brush box, a conductive support, a brush, and a conductive ring. The collector ring that can realize deicing when the rotor of a rotorcraft rotates is installed between the propeller assembly and the power assembly. When the signal and electric power are input to the brush via the fixed end cable, the brush is pressed onto the conductive ring by the pressure of the brush compression spring, and the signal and electric power are transmitted to the conductive support through the conductive pin, and finally the signal and electric power are transmitted to each blade of the propeller assembly via the rotor end cable connected to the conductive support. When the rotor rotates, these signals and electric power can also be transmitted to the rotor end cable through the collector ring, and then output to each blade of the propeller assembly, so as to heat the blade and input and output various signals, thereby achieving the effect of anti-deicing of the rotor propeller. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 The utility model is a schematic diagram of the position of the collector ring which can realize de-icing when the rotor of the rotorcraft rotates, and is installed between the rotor propeller and the engine.
[0020] Figure 2 for Figure 1 A local enlarged schematic diagram of the marked area.
[0021] Figure 3 The axial side schematic diagram of the split collector ring is provided to hide the partial structures such as the rotor propeller and the engine which are not related to the utility model.
[0022] Figure 4 For Figure 3 On this basis, a front view of a collector ring for deicing a rotorcraft rotor when the rotor rotates can be realized.
[0023] Figure 5 For Figure 3 On the basis of the above, a schematic top view of the collector ring for deicing the rotor of the rotorcraft when the rotor rotates can be realized.
[0024] Figure 6 for Figure 5 Cross-sectional view along the AA direction.
[0025] Figure 7 for Figure 6 A partial enlarged schematic diagram of the marked area.
[0026] Figure 8 For the general Figure 3 After further concealing part of the structure, an axial schematic diagram of the split collector ring for deicing when the rotor of the rotorcraft rotates can be realized.
[0027] Fig. 9 For the general Figure 8After further concealing part of the structure, an axial schematic diagram of the collector ring for de-icing the rotor of the rotorcraft when the rotor rotates can be realized.
[0028] Fig.10 For Fig. 9 On this basis, a front view of a collector ring for deicing a rotorcraft rotor when the rotor rotates can be realized.
[0029] Fig.11 for Fig.10 Cross-sectional view along the BB direction.
[0030] Fig.12 It is a schematic axial view of one side of the base cover 102 - 2 .
[0031] Fig.13 It is a schematic axial view of the assembly of the base covers 102 - 1 , 102 - 2 and the brush box 103 .
[0032] Fig.14 A schematic diagram of the axial side of the rotor 101 - 2 on one side.
[0033] Fig.15 It is a schematic diagram of the shaft side after the rotors 101 - 1 and 101 - 2 on both sides are assembled.
[0034] Fig.16 A schematic axial view of one side of the conductive ring 106 .
[0035] Fig.17 It is a schematic axial view after the conductive rings 106 on both sides are assembled with fasteners 183 .
[0036] Fig.18 Schematic diagram of the conductive support 104 - 1 .
[0037] In the figure: 100-collector ring for deicing the rotor of the rotorcraft when it rotates, 1011-rotor support, 101-1-first rotor, 101-2-second rotor, 102-1-base outer cover, 102-2-base outer cover, 103-brush box, 104-1-conductive support, 104-2-conductive support, 104-3-conductive support, 105-brush, 106-conductive ring, 181-base fastener, 182-conductive support fastener, 183-conductive ring fastener, 184-conductive pin, 191-fixed end cable, 192-rotor end cable, 193-brush compression spring, 200-propeller assembly, 201-propeller shaft, 300-power assembly. DETAILED DESCRIPTION
[0038] The specific implementation of the utility model is described in detail below with reference to the accompanying drawings.
[0039] like Figure 1 and2 As shown, the collector ring 100 provided by the embodiment of the utility model for realizing de-icing of the rotor of the rotorcraft during rotation is installed between the propeller assembly 200 and the power assembly 300. After the signal and the electric power are input to the split collector ring 100 via the fixed end cable 191, the specific process of the signal and the electric power being transmitted to each blade of the propeller assembly 200 through the collector ring 100 is as follows: When the signal and the electric power are input to the brush 105 via the fixed end cable 191, the brush 105 is pressed onto the conductive ring 106 by the pressure of the brush pressing spring 193, and the conductive ring 106 is pressed onto the conductive ring 106 by the conductive ring 106. The plug 184 transmits the signal and the electric power to the conductive support 104, and the rotor end cable 192 is fixedly connected to the conductive support 104. Finally, the signal and the electric power are transmitted to each blade of the propeller assembly 200 via the rotor end cable 192 connected to the conductive support 104. Even when the rotor is rotating, these signals and the electric power can be transmitted to the rotor end cable 192 through the collector ring 100, and then output to each blade of the propeller assembly 200, so as to heat the blades and input and output various signals, thereby achieving the effect of anti-deicing of the rotor propeller.
[0040] See also Figure 1 , Figure 2 , Figure 3 and Figure 4 The embodiment of the utility model provides a collector ring 100 that can realize de-icing when the rotor of a rotorcraft rotates, including: a rotor 101, a base cover 102, a brush box 103, N conductive supports 104 of different lengths, N brushes 105 and N conductive rings 106; N is the number of propeller blades; the rotor 101 is installed in the base cover 102; the base cover 102 is detachably installed on the power assembly 300, and the brush box 103 is installed on the base cover 102; the rotor 101 is fixed to the propeller assembly 200 through a rotor support 1011; the rotor 101, the base cover 102 and the brush box 103 are insulators; the conductive supports 104, the brushes 105 and the conductive rings 106 are conductors.
[0041] See Figure Figure 8 , Fig. 9 , Fig.10 , Fig.11 , Fig.14 and Fig.15 The rotor 101 includes a first rotor 101 - 1 and a second rotor 101 - 2 that are detachably connected; the first rotor 101 - 1 and the second rotor 101 - 2 are both provided with grooves on their outer walls, and the conductive ring 106 is installed in the groove, and the groove cooperates with one end of the conductive ring 106 .
[0042] See Figure Figure 6 and Fig.11, the conductive support 104 is electrically connected to the conductive ring 106 through the conductive pin 184, and the conductive pin 184 limits the conductive ring 106; the brush 105 transmits the signal and electric power to the conductive support 104 through the conductive pin 184; see Figure 5 , N conductive supports 104 are evenly distributed around the inner walls of the first rotor 101-1 and the second rotor 101-2; the conductive supports 104 and the inner sides of the rotor 101 are both arc surfaces; the arc surface of the conductive support 104 cooperates with the propeller shaft on the propeller assembly 200; a rotor-end cable 192 is provided on the conductive support 104, and the rotor-end cable 192 is fixed on the conductive support 104.
[0043] See also Figure 6 and Figure 7 , the brush box 103 is provided with a cable cavity and a plurality of brush cavities; the cable cavity has a cable hole, and the fixed end cable 191 passes through the cable cavity and out of the cable hole; each of the brush cavities accommodates one brush 105, one end of the brush 105 is connected to the fixed end cable 191, and is pressed into the brush cavity through the brush pressing spring 193, and the other end of the brush 105 has a conductive ring cavity, and the conductive ring cavity cooperates with the other end of the conductive ring 106; the brush 105 is pressed against the other end of the conductive ring 106 through the brush pressing spring 193; see Fig.16 Each of the conductive rings 106 includes two semicircular conductive rings with the same structure, and the two semicircular conductive rings are detachably connected.
[0044] The conductive supports 104 are evenly distributed around the rotors 101-1 and 101-2, and the number of the conductive supports 104, brushes 105, conductive rings 106 and cables 192 is usually the same as the number of blades. Among the components of the collector ring 100, the brushes 105, conductive rings 106, conductive supports 104 and conductive pins 184 are conductors, and the remaining components are insulators and are not conductive.
[0045] The rotor 101 is designed as a structure in which two pieces are spliced and installed, namely 101-1 and 101-2. The inner sides of both pieces can be designed as a 180° semicircular section for easy splicing and installation. The rotor 101 has grooves with the same number as the number of blades for installing the conductive ring 106. After the rotors 101-1 and 101-2 are spliced, they are fixedly connected to the propeller assembly by connecting the rotor support 1011. After being connected to the hub, they rotate together with the propeller assembly 200. Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 The rotor 101 of the collector ring has two independent structures, and the structure is designed with sealing measures, such as Figure 7 As shown in the marked part, no bearing is required between the two. The base housings 102-1 and 102-2 are mounted on the power assembly 300, and the brush box 103 is mounted on the base housing 102-1.
[0046] The conductive ring 106 is designed as a structure in which two pieces are spliced together and installed. The two pieces have the same structure and the inner side is designed as a 180° semicircular section for easy splicing and installation. Splicing and installation are particularly suitable for current and old aircraft with finalized designs. The collector ring can be installed without disassembling the engine and propeller. Fig.16 , 17 As shown, the conductive ring 106 is positioned by the conductive pin 184 to limit its rotation relative to the rotor 101. The conductive support 104 is evenly distributed around the conductive support rotors 101-1 and 101-2, and the inner side of the conductive support and the inner side of the rotor 101 are both arc surfaces, which cooperate with the propeller shaft 201 to cooperate with the relative rotation of the propeller shaft 201.
[0047] The utility model is characterized in that the rotor and the conductive ring are designed to be split, so that they are easy to install and disassemble, and have good maintainability. It is suitable for current and old models of rotorcraft with various structural finalizations and anti-icing requirements, and can be installed without disassembling the engine and propeller. The conductive pin can not only position the conductive ring in the annular direction, but also serve as a conductive carrier to transmit electrical energy and signals. It solves the problems of the traditional rotor anti-icing collector ring with complex structure, difficult installation, high cost, and high maintenance cost.
[0048] The utility model greatly improves maintainability and reduces maintenance costs, thereby increasing the service life, reliability and safety of the collector ring, the anti-icing system and even the entire rotorcraft. The utility model has strong structural adaptability and is very suitable for current and old rotorcraft with various structural finalizations and anti-icing requirements. It can be installed without disassembling the engine and propeller to improve the flight performance of various finalized or under-development rotorcraft and improve flight safety.
[0049] In the above embodiments, see Fig.16 and Fig.17 The semicircular conductive ring 106 is provided with a connecting ear, and the two semicircular conductive rings are detachably connected through the connecting ear. The conductive ring 106 is designed with a connecting ear, and after the two conductive rings 106 are spliced into the groove of the rotor 101, the two conductive rings 106 are fixed by the conductive ring fastener 183.
[0050] In the above embodiments, see Figure 6 , Fig.11 and Fig.18 The conductive ring 106 is provided with a conductive pin slot for accommodating the conductive pin 184. Fig.16 , 17 As shown, a limiting hole is designed in the conductive ring 106, and the conductive pin 184 is inserted into the positioning hole to position the conductive ring 106 to limit its rotation relative to the rotor 101. The structural limiting principle is as follows Figure 6 and 11 shown.
[0051] In the above embodiments, see Figure 6 Conductive support grooves are provided on the inner walls of the first rotor 101 - 1 and the second rotor 101 - 2 , and the conductive support 104 is installed in the conductive support grooves, which facilitates the positioning and installation of the conductive support 104 .
[0052] In the above embodiments, see Figure 6 and Figure 7 The rotor end cable 192 is fixed to the conductive support 104 through the conductive support fastener 182. The rotor 101 and the rotor support 1011 are bolted. Figure 8 The rotor 101 and the conductive support 104 are detachably connected via a conductive support fastener 182. In the above embodiment, the arc surface of the conductive support 104 is clearance-matched with the propeller shaft.
[0053] In the above embodiments, see Fig.12 and Fig.13 The base outer cover 102 includes a first base outer cover and a second base outer cover with the same structure and detachably connected.
[0054] In the above embodiments, see Figure 2 The first base cover and the second base cover are mounted on the power assembly 300 through the base fastener 181. The rotor support 1011 can be a structural part of the hub itself, or can be designed as an integral whole with the rotor 101, and its specific solution should not be used as a limitation to the present invention.
[0055] In the above embodiment, the base cover 2 is designed as a structure in which two pieces are spliced and installed, namely 102-1 and 102-2, and the inner sides of both pieces are designed as a 180° semicircular cross-section to facilitate splicing and installation.
[0056] In the above embodiment, among the structural parts of the collector ring 100, the conductive ring 106, the conductive support 104, and the conductive plug 184 can be made of conductive materials such as silver-copper-nickel alloy. The brush 105 can be made of copper-graphite composite material; the remaining structural parts and other components are insulators and can be formed of any of various non-conductive materials.
[0057] The utility model can realize the de-icing of the collector ring when the rotor of the rotorcraft rotates, including a rotor support, a rotor, a base cover, a brush box, a conductive support, a brush, and a conductive ring. The collector ring is installed between the propeller assembly and the power assembly. When the signal and electric power are input to the brush via the fixed end cable, the brush is pressed onto the conductive ring by the pressure of the brush compression spring, and the signal and electric power are transmitted to the conductive support through the conductive pin, and finally the signal and electric power are transmitted to each blade of the propeller assembly via the rotor end cable connected to the conductive support. When the rotor rotates, these signals and electric power can also be transmitted to the rotor end cable through the collector ring, and then output to each blade of the propeller assembly, so as to heat the blade and input and output various signals, thereby achieving the effect of anti-de-icing of the rotor propeller.
[0058] For those skilled in the art, it is obvious that the embodiments of the present invention are not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic features of the embodiments of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the embodiments of the present invention is limited by the attached claims rather than the above description, so it is intended to include all changes that fall within the meaning and scope of the equivalent elements of the claims in the embodiments of the present invention. Any figure mark in the claims should not be regarded as limiting the claims involved. In addition, it is obvious that the word "including" does not exclude other units or steps, and the singular does not exclude the plural. Multiple units, modules or devices stated in the system, device or terminal claims can also be implemented by the same unit, module or device through software or hardware. The words first, second, etc. are used to indicate the name, and do not indicate any specific order.
[0059] Finally, it should be noted that the above implementation modes are only used to illustrate the technical solutions of the embodiments of the utility model and are not limiting. Although the embodiments of the utility model are described in detail with reference to the above preferred implementation modes, ordinary technicians in this field should understand that the technical solutions of the embodiments of the utility model can be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the embodiments of the utility model.
Claims
1. A collector ring capable of deicing a rotorcraft rotor when it is rotating, characterized in that: include: A rotor, a base cover, a brush box, N conductive supports of different lengths, N brushes and N conductive rings; N is the number of propeller blades; The rotor is installed in the base cover; the base cover is detachably installed on the power assembly; the brush box is installed on the base cover; the rotor is fixed to the propeller assembly through a rotor support; the rotor, the base cover and the brush box are insulators; the conductive support, the brush and the conductive ring are conductors; The conductive support is electrically connected to the conductive ring through a conductive pin, a rotor end cable is provided on the conductive support, the rotor end cable is fixed on the conductive support, and the conductive pin limits the conductive ring; The brush box is provided with a cable cavity and a plurality of brush cavities; each of the brush cavities accommodates one brush, and one end of the brush is pressed into the brush cavity by the brush clamping spring; one end of the brush is connected to a fixed-end cable, and the fixed-end cable passes through the cable cavity; the other end of the brush has a conductive ring cavity, and the conductive ring cavity cooperates with the outer wall of the conductive ring; the brush is pressed against the outer wall of the conductive ring by the brush clamping spring; the inner side surface of the conductive support cooperates with the propeller shaft on the propeller assembly; the brush transmits signals and electrical power to the conductive support through the conductive pin.
2. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 1, characterized in that: The rotor includes a first rotor and a second rotor that are detachably connected.
3. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 2, characterized in that: Each of the conductive rings comprises two semicircular conductive rings with the same structure, and the two semicircular conductive rings are detachably connected.
4. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 3, characterized in that: The semicircular conductive ring is provided with a connecting ear piece, and the connecting ear piece is connected by a detachable conductive ring fastener.
5. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 1, characterized in that: The base outer cover comprises a first base outer cover and a second base outer cover which have the same structure and are detachably connected.
6. The slip ring capable of deicing a rotorcraft rotor when it rotates according to claim 5, characterized in that: The first base housing and the second base housing are mounted on the power assembly via base fasteners.
7. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 2, characterized in that: Conductive support grooves are provided on the inner walls of the first rotor and the second rotor, and the conductive support is installed in the conductive support grooves.
8. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 1, characterized in that: The rotor end cable is fixed on the conductive support by a conductive support fastener.
9. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 1, characterized in that: The rotor and the conductive support are detachably connected via a conductive support fastener.
10. The slip ring capable of achieving de-icing when the rotor of a rotary-wing aircraft rotates according to claim 2, characterized in that: The outer walls of the first rotor and the second rotor are both provided with grooves, the conductive rings are installed in the grooves, and the grooves are matched with the outer walls of the conductive rings.