Hybrid energy power system suitable for vertical take-off and landing
By adopting a hybrid energy power system in a vertical take-off and landing aircraft, and utilizing the advantages of fuel cells and lithium batteries, the problem of low energy density of lithium batteries resulting in short cruising mileage is solved, and the efficient performance of the aircraft in take-off and landing and cruising states is achieved.
Patent Information
- Application Number
- CN202411941848.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-26
- Publication Date
- 2025-04-11
AI Technical Summary
The existing vertical take-off and landing vehicles have low energy density, resulting in short cruising mileage, making it difficult to meet the needs of long-distance flights.
The hybrid energy power system is adopted, and the power device is driven in parallel through the fuel cell device and the lithium battery device. In the take-off and landing state, it mainly relies on the rate discharge of lithium batteries to ensure the smooth take-off and landing of the aircraft; in the cruise state, it mainly relies on the high energy density of fuel cells to extend the cruising range of the aircraft.
Through the hybrid energy power system, the aircraft can ensure smooth take-off and landing in the take-off and landing state, and extend the flight distance in the cruise state, improving overall performance.
Smart Images
Figure CN119796503A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the field of aircraft, and in particular to a hybrid energy power system suitable for vertical take-off and landing. Background Art
[0002] In the related art, vertical take-off and landing aircraft are driven by lithium batteries to meet the power required for vertical take-off and landing and hovering. However, the energy density of lithium batteries is low, resulting in a short cruising range of vertical take-off and landing aircraft. Summary of the invention
[0003] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.
[0004] To this end, an embodiment of the present invention proposes a hybrid energy power system suitable for vertical take-off and landing.
[0005] The hybrid energy power system suitable for vertical take-off and landing of the embodiment of the present invention comprises:
[0006] A power device, a fuel cell device and a lithium battery device, wherein the fuel cell device and the lithium battery device are connected in parallel to the power device, and both the fuel cell device and the lithium battery device are used to drive the power device.
[0007] The hybrid energy power system suitable for vertical take-off and landing of the embodiment of the present invention drives the power device through a fuel cell device and a lithium battery device. The rate discharge of the lithium battery device ensures that the aircraft can take off and land smoothly, and the fuel cell device has a high energy density so that the aircraft has a longer cruising range.
[0008] In some embodiments, the hybrid energy power system suitable for vertical take-off and landing includes a take-off and landing state and a cruising state.
[0009] In the take-off and landing state, the power provided by the lithium battery device to the power device accounts for 70% or more of the total power provided by the fuel cell device and the lithium battery device to the power device.
[0010] In the cruising state, the power provided by the fuel cell device to the power device accounts for 70% or more of the total power provided by the fuel cell device and the lithium battery device to the power device.
[0011] In some embodiments, the fuel cell device is electrically connected to the lithium battery device for supplying power to the lithium battery device.
[0012] In some embodiments, the fuel cell device includes a fuel container, a fuel cell body and a power distribution unit, the fuel container is connected to the fuel cell body for supplying fuel to the fuel cell body, and the power distribution unit is electrically connected to the fuel cell body, the lithium battery device and the power device, respectively, for supplying power from the fuel cell body to the power device and / or the lithium battery device.
[0013] In some embodiments, the fuel cell device is a hydrogen fuel cell device.
[0014] In some embodiments, the fuel container is a liquid hydrogen container.
[0015] In some embodiments, the lithium battery device includes a lithium battery body and a DC-DC converter, and the DC-DC converter is electrically connected to the lithium battery body, the fuel cell device, and the power device, respectively, and is used to supply power from the lithium battery body to the power device, and to supply power from the fuel cell device to the lithium battery body.
[0016] In some embodiments, when the fuel cell device fails, the aircraft lands in a vertical landing posture, and when the lithium battery device fails, the aircraft lands in a smooth landing posture.
[0017] In some embodiments, there are at least two power devices, each of which is connected to the fuel cell device and the lithium battery device.
[0018] In some embodiments, the power device includes a busbar and at least two power components connected in parallel to the busbar, the power components include an inverter, a rotating motor and a rotary wing connected in sequence, and the inverter is electrically connected to the busbar. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a schematic diagram of a hybrid energy power system suitable for vertical take-off and landing according to an embodiment of the present invention.
[0020] Reference numerals:
[0021] 1. Power device; 11. Busbar; 12. Inverter; 13. Rotating motor; 14. Rotating wing; 2. Fuel cell device; 21. Fuel container; 22. Fuel cell body; 23. Power distribution unit; 3. Lithium battery device; 31. Lithium battery body; 32. DC-DC converter. DETAILED DESCRIPTION
[0022] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.
[0023] Reference below Figure 1 A hybrid energy power system suitable for vertical take-off and landing according to an embodiment of the present invention is described.
[0024] It should be noted that the hybrid energy power system suitable for vertical take-off and landing of the embodiment of the present invention is preferably, but not limited to, applied to vertical take-off and landing aircraft, and is more preferably applied to rotary-wing vertical take-off and landing aircraft.
[0025] like Figure 1 As shown, the hybrid energy power system suitable for vertical take-off and landing according to an embodiment of the present invention includes a power device 1, a fuel cell device 2 and a lithium battery device 3.
[0026] The fuel cell device 2 and the lithium battery device 3 are connected in parallel to the power device 1, and both the fuel cell device 2 and the lithium battery device 3 are used to drive the power device 1. For example, Figure 1 As shown, the fuel cell device 2 and the lithium battery device 3 are both electrically connected to the power device 1 and connected in parallel to the power input end of the power device 1 to drive the power device 1 to operate and generate power.
[0027] The hybrid energy power system suitable for vertical take-off and landing of the embodiment of the present invention drives the power device through a fuel cell device and a lithium battery device. The rate discharge of the lithium battery device ensures that the aircraft can take off and land smoothly, and the fuel cell device has a high energy density so that the aircraft has a longer cruising range.
[0028] In some embodiments, a hybrid energy power system suitable for vertical take-off and landing includes a take-off and landing state and a cruising state. In the take-off and landing state, the power provided by the lithium battery device 3 to the power device 1 accounts for 70% or more of the total power provided by the fuel cell device 2 and the lithium battery device 3 to the power device 1. In the cruising state, the power provided by the fuel cell device 2 to the power device 1 accounts for 70% or more of the total power provided by the fuel cell device 2 and the lithium battery device 3 to the power device 1.
[0029] like Figure 1 As shown, the hybrid energy power system suitable for vertical take-off and landing includes a take-off and landing state and a cruising state. In other words, the aircraft has two working conditions: a take-off and landing state and a cruising state. The take-off and landing state includes the state of the aircraft in the take-off phase and the state of the aircraft in the landing phase. The cruising state is the state of the aircraft between the take-off phase and the landing phase, entering the predetermined route and maintaining stable flight.
[0030] In the take-off and landing state, the power provided by the lithium battery device 3 to the power device 1 accounts for 70% or more of the total power provided by the fuel cell device 2 and the lithium battery device 3 to the power device 1, such as 70%, 75%, 80%, 90%, 95%, etc., and the power provided by the fuel cell device 2 to the power device 1 accounts for less than 30% of the total power. In other words, in the take-off and landing state, the lithium battery device 3 mainly provides power to the power device 1 to drive the power device 1, and the fuel cell device 2 plays an auxiliary role. Thus, the rate discharge of the lithium battery device 3 ensures that the aircraft can take off and land smoothly.
[0031] In the cruising state, the power provided by the fuel cell device 2 to the power device 1 accounts for 70% or more of the total power, such as 70%, 75%, 80%, 90%, 95%, etc., and the power provided by the lithium battery device 3 to the power device 1 accounts for less than 30% of the total power. In other words, in the take-off and landing state, the fuel cell device 2 mainly provides electricity to the power device 1 to drive the power device 1, and the lithium battery device 3 plays an auxiliary role. Thus, the higher energy density of the fuel cell device 2 enables the aircraft to have a longer cruising range.
[0032] In some embodiments, the fuel cell device 2 is electrically connected to the lithium battery device 3 to supply power to the lithium battery device 3 .
[0033] like Figure 1 As shown, the fuel cell device 2 is electrically connected to the lithium battery device 3, so that the lithium battery device 3 can be charged by the fuel cell device 2, so that the lithium battery device 3 can ensure smooth take-off and landing of the aircraft, especially smooth landing.
[0034] Preferably, but not limited to, in the cruising state, when there is a deviation between the flight margin of the lithium battery device 3 and the estimated value of the flight management system of the aircraft, the output power of the fuel cell device 2 is increased, and the fuel cell device 2 supplies power to the lithium battery device 3, thereby driving the power device 1 and charging the lithium battery device 3 at the same time. When the flight margin of the lithium battery device 3 reaches the estimated value of the flight management system, the fuel cell device 2 stops supplying power to the lithium battery device 3 and recovers to the output power before supplying power to the lithium battery device 3, thereby stopping charging the lithium battery device 3 and continuing to drive the power device 1.
[0035] After the aircraft lands, the fuel of the fuel cell device 2 and the power of the lithium battery device 3 are replenished through external equipment.
[0036] In some embodiments, the fuel cell device 2 includes a fuel container 21, a fuel cell body 22 and a power distribution unit 23. The fuel container 21 is connected to the fuel cell body 22 for supplying fuel to the fuel cell body 22. The power distribution unit 23 is electrically connected to the fuel cell body 22, the lithium battery device 3 and the power device 1 respectively for supplying power from the fuel cell body 22 to the power device 1 and / or the lithium battery device 3.
[0037] like Figure 1 As shown, the fuel container 21 is connected to the fuel cell body 22 through a pipeline, so that the fuel container 21 provides fuel to the fuel cell body 22 to generate electricity.
[0038] The fuel cell body 22, the lithium battery device 3 and the power device 1 are all electrically connected to the power distribution unit 23. The power distribution unit 23 receives the electricity generated by the fuel cell body 22 and distributes it to both the lithium battery device 3 and the power device 1 or only to the power device 1. When the power distribution unit 23 distributes electricity to both the lithium battery device 3 and the power device 1, the fuel cell body 22 simultaneously drives the power device 1 and charges the lithium battery device 3. When the power distribution unit 23 distributes electricity only to the power device 1, the fuel cell body 22 drives the power device 1 without charging the lithium battery device 3.
[0039] In some embodiments, the fuel cell device 2 is a hydrogen fuel cell device 2, thereby avoiding air pollution.
[0040] Specifically, the fuel cell body 22 is a hydrogen fuel cell, and the fuel container 21 is a hydrogen storage container. In other words, the fuel is hydrogen.
[0041] Preferably, the fuel container 21 is a liquid hydrogen container, in other words, hydrogen is stored in the fuel container 21 in a liquid state, so that the fuel container 21 has a higher volume-to-weight ratio, so that the aircraft has a lower deadweight and a higher payload.
[0042] In some embodiments, the lithium battery device 3 includes a lithium battery body 31 and a DC-DC converter 32. The DC-DC converter 32 is electrically connected to the lithium battery body 31, the fuel cell device 2, and the power device 1, respectively, and is used to supply power from the lithium battery body 31 to the power device 1, and to supply power from the fuel cell device 2 to the lithium battery body 31.
[0043] like Figure 1As shown, the lithium battery body 31, the power distribution unit 23 of the fuel cell device 2, and the power device 1 are all electrically connected to the DC-DC converter 32. The DC-DC converter 32 can receive the power generated by the lithium battery body 31 and supply it to the power device 1, so that the lithium battery body 31 drives the power device 1. The DC-DC converter 32 can also receive the power distributed by the power distribution unit 23 and supply it to the lithium battery body 31, so that the fuel cell body 22 charges the lithium battery body 31.
[0044] Furthermore, the number of lithium battery bodies 31 is preferably at least two, the fuel cell body 22 charges some of the lithium battery bodies 31 , and the remaining lithium battery bodies 31 drive the power device 1 .
[0045] In some embodiments, when the fuel cell device 2 fails, the device lands in a vertical landing posture, and when the lithium battery device 3 fails, the device lands in a smooth landing posture.
[0046] Specifically, when the fuel cell device 2 of the hybrid energy power system suitable for vertical take-off and landing fails in the cruising state, the lithium battery device 3 can still discharge at a multiple rate to ensure smooth take-off and landing, so the aircraft lands in a vertical landing posture. In other words, the aircraft is in a vertical posture during the landing phase.
[0047] When the lithium battery device 3 of the hybrid energy power system suitable for vertical take-off and landing fails in the cruising state, the lithium battery device 3 cannot discharge at a normal rate, and the fuel cell device 2 cannot discharge at a rate. Therefore, the aircraft uses the wings to provide lift and lands in a smooth landing posture. In other words, the aircraft is in a smooth posture during the landing phase.
[0048] This ensures that the aircraft can land smoothly.
[0049] In some embodiments, there are at least two power devices 1 , and each power device 1 is connected to a fuel cell device 2 and a lithium battery device 3 .
[0050] like Figure 1 As shown, the power devices 1 are preferably but not limited to being two connected in parallel, and the fuel cell device 2 and the lithium battery device 3 are electrically connected to each power device 1. When one of the power devices 1 fails, the other power device 1 can still operate normally to ensure the cruising and landing of the aircraft.
[0051] In some embodiments, the power device 1 includes a bus 11 and at least two power components connected in parallel to the bus 11 . The power components include an inverter 12 , a rotating motor 13 and a rotary wing 14 connected in sequence. The inverter 12 is electrically connected to the bus 11 .
[0052] like Figure 1As shown, the power device 1 includes a busbar 11 and a power assembly. The busbar 11 is electrically connected to the fuel cell device 2 and the lithium battery device 3. The power assembly is preferably but not limited to two connected in parallel to the busbar 11. The power assembly includes an inverter 12, a rotating motor 13 and a rotary wing 14 connected in sequence. The inverter 12 is electrically connected between the busbar 11 and the rotating motor 13 to supply power to the rotating motor 13. The rotating shaft of the rotating motor 13 is connected to the rotary wing 14, thereby driving the rotary wing 14 to rotate.
[0053] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0054] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.
[0055] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.
Claims
1. A hybrid energy power system suitable for vertical take-off and landing, characterized in that: include: A power device (1), a fuel cell device (2) and a lithium battery device (3), wherein the fuel cell device (2) and the lithium battery device (3) are connected in parallel to the power device (1), and the fuel cell device (2) and the lithium battery device (3) are both used to drive the power device (1).
2. The hybrid energy power system suitable for vertical take-off and landing according to claim 1, characterized in that: Including take-off and landing status and cruising status, In the take-off and landing state, the power provided by the lithium battery device (3) to the power device (1) accounts for 70% or more of the total power provided by the fuel cell device (2) and the lithium battery device (3) to the power device (1), In the cruising state, the power provided by the fuel cell device (2) to the power device (1) accounts for 70% or more of the total power provided by the fuel cell device (2) and the lithium battery device (3) to the power device (1).
3. The hybrid energy power system suitable for vertical take-off and landing according to claim 1, characterized in that: The fuel cell device (2) is electrically connected to the lithium battery device (3) and is used to supply power to the lithium battery device (3).
4. The hybrid energy power system suitable for vertical take-off and landing according to claim 3, characterized in that: The fuel cell device (2) comprises a fuel container (21), a fuel cell body (22) and a power distribution unit (23); the fuel container (21) is connected to the fuel cell body (22) and is used to supply fuel to the fuel cell body (22); the power distribution unit (23) is electrically connected to the fuel cell body (22), the lithium battery device (3) and the power device (1) respectively and is used to supply power from the fuel cell body (22) to the power device (1) and / or the lithium battery device (3).
5. The hybrid energy power system suitable for vertical take-off and landing according to claim 1, characterized in that: The fuel cell device (2) is a hydrogen fuel cell device (2).
6. The hybrid energy power system suitable for vertical take-off and landing according to claim 4, characterized in that: The fuel container (21) is a liquid hydrogen container.
7. The hybrid energy power system suitable for vertical take-off and landing according to claim 3, characterized in that: The lithium battery device (3) comprises a lithium battery body (31) and a DC-DC converter (32); the DC-DC converter (32) is electrically connected to the lithium battery body (31), the fuel cell device (2), and the power device (1), respectively, and is used to supply power from the lithium battery body (31) to the power device (1), and to supply power from the fuel cell device (2) to the lithium battery body (31).
8. The hybrid energy power system suitable for vertical take-off and landing according to claim 1, characterized in that: When the fuel cell device (2) fails, the vehicle lands in a vertical landing posture; when the lithium battery device (3) fails, the vehicle lands in a smooth landing posture.
9. The hybrid energy power system suitable for vertical take-off and landing according to claim 1, characterized in that: There are at least two power devices (1), and each of the power devices (1) is connected to the fuel cell device (2) and the lithium battery device (3).
10. The hybrid energy power system suitable for vertical take-off and landing according to claim 9, characterized in that: The power device (1) comprises a busbar (11) and at least two power components connected in parallel to the busbar (11), the power components comprising an inverter (12), a rotating motor (13) and a rotary wing (14) connected in sequence, and the inverter (12) is electrically connected to the busbar (11).