Distribution system of distributed propulsion electric aircraft

Abstract

The invention discloses a power distribution system of a distributed propulsion electric aircraft, which belongs to the technical field of aircraft power distribution systems and comprises two groups of power supply components arranged on two sides of the aircraft in a mirroring manner. Each group of power supply components consists of at least one power supply link; a plurality of groups of emergency switches are also included; the two groups of power supply links arranged on the two sides of the airplane in a mirroring manner are electrically connected through emergency switches, or the power supply links on the two sides are arranged in sequence from left to right, and the adjacent power supply links are electrically connected through emergency switches, or the interiors of the power supply links are electrically connected through emergency switches, or the power supply links on the two sides are respectively arranged in sequence from left to right; the power supply link n on one side is electrically connected with the power supply link n on the other side through an emergency switch, or the power supply links on the two sides are arranged in sequence from left to right, and each power supply link n is electrically connected with (n-1) power supply links through emergency switches; by means of the mode, when power grid components of the power battery of the aircraft are lost, the propelling device can continuously generate thrust / lift force through emergency power distribution.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft power distribution systems, and in particular to a power distribution system for a distributed propulsion electric aircraft. Background Art

[0002] At present, there are a wide variety of models and configurations of electric aircraft under development, and the technical paths behind them are different, but the use of distributed propulsion technology has initially formed a mainstream technical trend. Distributed propulsion electric aircraft replace the traditional single high-power engine with multiple small electric engines, which not only improves the aerodynamic efficiency and carrying capacity of the aircraft, but also significantly reduces environmental pollution and noise levels. In addition, the electric propulsion system of electric aircraft also has the characteristics of high power and high reliability requirements. Therefore, the energy transmission and control architecture from power batteries to propulsion devices is usually realized by high-voltage DC grid distribution technology.

[0003] Among many existing technologies, Chinese patent application CN207977738U discloses a low-voltage DC power distribution system for a general aircraft power distribution area, which includes a bus, a contactor, a rack, a voltage device, and a current measuring device. The bus includes an important bus, a general bus, and an emergency bus. The generator directly transmits electrical energy to the electrical equipment of the general aircraft through the bus. An electric mechanical contactor driven by an internal logic and a bidirectional current sensor is connected between the important bus and the general bus.

[0004] However, this patent application cannot achieve dynamic reconstruction of power distribution, which can ensure that when the aircraft power battery grid components are lost, the propulsion device can continue to generate thrust / lift through emergency power distribution.

[0005] Based on this, the present invention designs a power distribution system for a distributed propulsion electric aircraft to solve the above problems. Summary of the invention

[0006] In view of the above-mentioned shortcomings of the prior art, the present invention provides a power distribution system for a distributed propulsion electric aircraft.

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0008] A power distribution system for a distributed propulsion electric aircraft includes two sets of power supply components mirror-imaged on both sides of the aircraft;

[0009] Each group of power supply components consists of at least one power supply link;

[0010] It also includes multiple sets of emergency switches;

[0011] The two groups of power supply links mirrored on both sides of the aircraft are electrically connected through an emergency switch or the power supply links on both sides are arranged in sequence from left to right, the adjacent power supply links are electrically connected through an emergency switch or the power supply links are electrically connected through an emergency switch or the power supply links on both sides are arranged in sequence from left to right, the power supply link n on one side is electrically connected to the power supply link n on the other side through an emergency switch or the power supply links on both sides are arranged in sequence from left to right, and each power supply link n is electrically connected to n-1 power supply links through an emergency switch;

[0012] n represents the nth group of power supply links;

[0013] The power supply link includes at most two power batteries, at most two propulsion devices, at most two normal switches and wires. The power batteries are electrically connected to the normal switches through wires, the normal switches are electrically connected to at least one propulsion device, and both ends of the emergency switch are electrically connected to two groups of wires respectively.

[0014] Furthermore, the propulsion device is a ducted motor fan.

[0015] Furthermore, when the power supply link includes a power battery, a propulsion device and a normal switch, the two ends of the emergency switch are electrically connected to the wires arranged in a mirror image on both sides of the aircraft.

[0016] Furthermore, when the power supply link includes a power battery, two propulsion devices and a normal switch, the power battery is electrically connected to the normal switch through a wire, the normal switch is electrically connected to both propulsion devices, and both ends of the emergency switch are electrically connected to wires mirrored on both sides of the aircraft.

[0017] Furthermore, when the power supply link includes two power batteries, a propulsion device and two normal switches, the two power batteries are electrically connected to the two normal switches through wires, and the two ends of the emergency switch are electrically connected to the wires mirror-set on both sides of the aircraft.

[0018] Furthermore, when the power supply link includes two power batteries, a propulsion device and two normal switches, the two power batteries are electrically connected to the two normal switches through wires, and the wires on both sides are arranged in sequence from left to right, and the two ends of the emergency switch are electrically connected to the nth wire on one side and the nth wire on the other side.

[0019] Furthermore, when the power supply link includes two power batteries, a propulsion device and two normal switches, the two power batteries are electrically connected to the two normal switches through wires, and the two ends of the emergency switch are electrically connected to the two wires of the power supply link.

[0020] Furthermore, when the power supply link includes a power battery, a propulsion device and a normal switch, the wires on both sides are arranged in sequence from left to right, and the two ends of the emergency switch are electrically connected to the two adjacent wires respectively.

[0021] Furthermore, when the power supply link includes a power battery, a propulsion device and a normal switch, the wires on both sides are arranged in sequence from left to right, and each wire is electrically connected to n-1 wires through an emergency switch.

[0022] Furthermore, the normal switch is a relay.

[0023] Compared with the prior art, the present invention has the following beneficial effects: 1. When the present invention is used, the power battery is controlled by a normal switch to supply power to the propulsion device. When the power battery fails, the two wires are connected by an emergency switch, so that the power battery that is not at fault can supply power to the two propulsion devices at the same time. Therefore, by dynamically reconstructing the power distribution considering the aircraft trim on the basis of the distributed direct distribution network, it can be ensured that when the aircraft power battery grid components are lost, the propulsion device can continue to generate thrust / lift through the emergency power distribution. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0025] Figure 1 A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 1 ;

[0026] Figure 2 A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 2 ;

[0027] Figure 3 A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 3 ;

[0028] Figure 4 A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 4 ;

[0029] Figure 5 A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 5 ;

[0030] Figure 6A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 6 ;

[0031] Figure 7 A block diagram of a power distribution system for a distributed propulsion electric aircraft of the present invention Figure 7 .

[0032] The numbers in the figure represent:

[0033] 1. Power battery 2. Propulsion device 3. Normal switch 4. Emergency switch 5. Wire. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] Embodiment 1: In some embodiments, please refer to the drawings of the specification Figure 1-Figure 7 , a power distribution system for a distributed propulsion electric aircraft, including two sets of power supply components mirror-imaged on both sides of the aircraft;

[0036] Each group of power supply components consists of at least one power supply link;

[0037] Also includes multiple sets of emergency switches 4;

[0038] The two groups of power supply links mirrored on both sides of the aircraft are electrically connected through the emergency switch 4 or the power supply links on both sides are arranged in sequence from left to right, the adjacent power supply links are electrically connected through the emergency switch 4 or the power supply links are electrically connected through the emergency switch 4 or the power supply links on both sides are arranged in sequence from left to right, the power supply link n on one side is electrically connected to the power supply link n on the other side through the emergency switch 4 or the power supply links on both sides are arranged in sequence from left to right, and each power supply link n is electrically connected to n-1 power supply links through the emergency switch 4;

[0039] n represents the nth group of power supply links;

[0040] The power supply link includes at most two power batteries 1, at most two propulsion devices 2, at most two normal switches 3 and wires 5. The power batteries 1 are electrically connected to the normal switches 3 through the wires 5, the normal switches 3 are electrically connected to at least one propulsion device 2, and both ends of the emergency switch 4 are electrically connected to two groups of wires 5 respectively.

[0041] When the present invention is in use, the power battery 1 is controlled by the normal switch 3 to supply power to the propulsion device 2. When the power battery 1 fails, the two wires 5 are turned on by the emergency switch 4, so that the power battery 1 that is not at fault can supply power to the two propulsion devices 2 at the same time. Therefore, by dynamically reconstructing the power distribution considering the aircraft trim on the basis of the distributed direct distribution network, it can be ensured that when the power grid components of the aircraft power battery 1 are lost, the propulsion device 2 can continue to generate thrust / lift through the emergency power distribution.

[0042] Embodiment 2: In some embodiments, Figure 1-Figure 7 As shown, as a preferred embodiment of the present invention, the propulsion device 2 is a ducted motor fan.

[0043] The normal switch 3 is a relay.

[0044] Embodiment 3: In some embodiments, Figure 1-Figure 7 As shown, as a preferred embodiment of the present invention, when the power supply link includes a power battery 1, a propulsion device 2 and a normal switch 3, the two ends of the emergency switch 4 are electrically connected to the wires 5 mirror-set on both sides of the aircraft.

[0045] When the power supply link includes a power battery 1, two propulsion devices 2 and a normal switch 3, the power battery 1 is electrically connected to the normal switch 3 through a wire 5, the normal switch 3 is electrically connected to both propulsion devices 2, and both ends of the emergency switch 4 are electrically connected to the wires 5 mirror-set on both sides of the aircraft.

[0046] When the power supply link includes two power batteries 1, a propulsion device 2 and two normal switches 3, the two power batteries 1 are electrically connected to the two normal switches 3 through wires 5, and the two ends of the emergency switch 4 are electrically connected to the wires 5 mirror-set on both sides of the aircraft.

[0047] When the power supply link includes two power batteries 1, a propulsion device 2 and two normal switches 3, the two power batteries 1 are electrically connected to the two normal switches 3 through wires 5, and the wires 5 on both sides are arranged in sequence from left to right. The two ends of the emergency switch 4 are electrically connected to the nth wire 5 on one side and the nth wire 5 on the other side.

[0048] When the power supply link includes two power batteries 1, a propulsion device 2 and two normal switches 3, the two power batteries 1 are electrically connected to the two normal switches 3 through wires 5, and both ends of the emergency switch 4 are electrically connected to the two wires 5 of the power supply link.

[0049] When the power supply link includes a power battery 1, a propulsion device 2 and a normal switch 3, the wires 5 on both sides are arranged in sequence from left to right, and the two ends of the emergency switch 4 are electrically connected to the two adjacent wires 5 respectively.

[0050] When the power supply link includes a power battery 1, a propulsion device 2 and a normal switch 3, the wires 5 on both sides are arranged in sequence from left to right, and each wire 5 is electrically connected to n-1 wires 5 through the emergency switch 4.

[0051] When the present invention is used, Figure 1 The scheme 1 shown is used in the case where the power battery 1 and the propulsion device 2 correspond one to one. At this time, the power battery 1 directly supplies power to the propulsion device 2 one to one. Under normal circumstances, the emergency switch 4 is in a normally disconnected state, and each group of power supply links is physically isolated and independently controlled. In an emergency situation, if a power battery 1 fails, the corresponding emergency switch 4 will be closed, and the power battery 1 in the corresponding mirror position will simultaneously supply power to the two mirror position propulsion devices 2. Regardless of whether this power supply adopts a power reduction strategy or a reserved power strategy, it can ensure that the aircraft has thrust or lift balance on both sides, thereby reducing dependence on the flight control system trim, and there is no need for the propulsion devices 2 in other positions to reduce their own power to maintain balance. This power distribution system can minimize the impact of the loss of power battery 1 on the overall thrust / lift and balance of the aircraft.

[0052] When the present invention is used, Figure 2 The second scheme shown is used in the case where the power battery 1 and the propulsion device 2 are one-to-two, and the effect of this scheme is similar to that of the first scheme;

[0053] When the present invention is used, Figure 3 In the scheme three shown, the energy density and efficiency of the entire distributed electric propulsion system are reduced. Because for the same number and power of propulsion devices 2, the corresponding number of power batteries 1 and power grid devices is multiplied. Even if the energy of a single power battery 1 can be reduced accordingly, the overall increase is still due to the addition of additional mechanical structures and electrical devices, resulting in weight and cost, and reducing the overall energy density. This configuration is often applicable to situations where the energy of a single power battery 1 is limited and multiple power batteries 1 need to be connected in parallel to increase the total amount of energy. The effect of this scheme is similar to that of scheme one.

[0054] When the present invention is used, Figure 5 , Figure 6 The schemes 5 and 6 shown are capable of realizing that when any power battery 1 fails, the adjacent power batteries 1 can be supplied with emergency power through the emergency switch 4 and the wire 5 .

[0055] When the present invention is used, Figure 7The scheme seven shown is a fully connected power distribution topology architecture in which n power batteries 1 supply power to n propulsion devices 2. When any power battery 1 is lost, any one or more of the remaining n-1 power batteries 1 can supply power to the corresponding propulsion device 2 through the emergency switch 4, and even an "n-1 supplies n" emergency power distribution architecture can be constructed, so that the propulsion device 2 of the whole machine can maximize the use of the remaining power on the basis of the balanced power of the whole machine. At the same time, this power distribution architecture can also achieve the most sufficient and balanced emergency power distribution for the scenario where multiple power batteries 1 are lost, such as "n supplies n-1" or "n supplies n-2", etc., to avoid the failure of the thrust device when the redundant power distribution groups in the above-mentioned power distribution architecture fail at the same time;

[0056] The use of a fully connected power distribution topology can better mitigate and accommodate the impact of multiple power battery 1 grid component failure events on the aircraft safety, and achieve balanced and efficient aircraft thrust / lift performance.

[0057] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements will not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A power distribution system for a distributed propulsion electric aircraft, characterized in that: It includes two sets of power supply components mirrored on both sides of the aircraft; Each group of power supply components consists of at least one power supply link; Also includes multiple groups of emergency switches (4); The two groups of power supply links arranged in mirror image on both sides of the aircraft are electrically connected via an emergency switch (4) or the power supply links on both sides are arranged in sequence from left to right, the adjacent power supply links are electrically connected via an emergency switch (4) or the power supply links are electrically connected inside the power supply links via an emergency switch (4) or the power supply links on both sides are arranged in sequence from left to right, the power supply link n on one side is electrically connected to the power supply link n on the other side via an emergency switch (4) or the power supply links on both sides are arranged in sequence from left to right, and each power supply link n is electrically connected to n-1 power supply links via an emergency switch (4); n represents the nth group of power supply links; The power supply link comprises at most two power batteries (1), at most two propulsion devices (2), at most two normal switches (3) and wires (5); the power batteries (1) are electrically connected to the normal switches (3) via the wires (5); the normal switches (3) are electrically connected to at least one propulsion device (2); and both ends of the emergency switch (4) are electrically connected to the two sets of wires (5) respectively.

2. The power distribution system for a distributed propulsion electric aircraft according to claim 1, characterized in that: The propulsion device (2) is a ducted motor fan.

3. The power distribution system for a distributed propulsion electric aircraft according to claim 2, characterized in that: When the power supply link includes a power battery (1), a propulsion device (2) and a normal switch (3), two ends of the emergency switch (4) are electrically connected to wires (5) arranged in mirror images on both sides of the aircraft.

4. The power distribution system for a distributed propulsion electric aircraft according to claim 3, characterized in that: When the power supply link comprises a power battery (1), two propulsion devices (2) and a normal switch (3), the power battery (1) and the normal switch (3) are electrically connected via a wire (5), the normal switch (3) and the two propulsion devices (2) are electrically connected, and both ends of the emergency switch (4) are electrically connected to the wires (5) arranged in a mirror image on both sides of the aircraft.

5. The power distribution system for a distributed propulsion electric aircraft according to claim 4, characterized in that: When the power supply link comprises two power batteries (1), a propulsion device (2) and two normal switches (3), the two power batteries (1) are electrically connected to the two normal switches (3) via wires (5), and the two ends of the emergency switch (4) are electrically connected to the wires (5) arranged in a mirror image on both sides of the aircraft.

6. The power distribution system for a distributed propulsion electric aircraft according to claim 5, characterized in that: When the power supply link comprises two power batteries (1), a propulsion device (2) and two normal switches (3), the two power batteries (1) are electrically connected to the two normal switches (3) via wires (5), the wires (5) on both sides are arranged in sequence from left to right, and the two ends of the emergency switch (4) are electrically connected to the nth wire (5) on one side and the nth wire (5) on the other side.

7. The power distribution system for a distributed propulsion electric aircraft according to claim 6, characterized in that: When the power supply link comprises two power batteries (1), a propulsion device (2) and two normal switches (3), the two power batteries (1) are respectively electrically connected to the two normal switches (3) via wires (5), and both ends of the emergency switch (4) are respectively electrically connected to the two wires (5) of the power supply link.

8. The power distribution system for a distributed propulsion electric aircraft according to claim 7, characterized in that: When the power supply link includes a power battery (1), a propulsion device (2) and a normal switch (3), the wires (5) on both sides are arranged in sequence from left to right, and the two ends of the emergency switch (4) are electrically connected to two adjacent wires (5) respectively.

9. The power distribution system for a distributed propulsion electric aircraft according to claim 8, characterized in that: When the power supply link includes a power battery (1), a propulsion device (2) and a normal switch (3), the wires (5) on both sides are arranged in sequence from left to right, and each wire (5) is electrically connected to n-1 wires (5) via an emergency switch (4).

10. The power distribution system for a distributed propulsion electric aircraft according to claim 9, characterized in that: The normal switch (3) is a relay.

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