BATTERY HOLDING DEVICE, BATTERY SYSTEM, AIRCRAFT AND METHOD FOR CHANGING A BATTERY FOR AN AIRCRAFT

Abstract

A battery holding device for an electrically driven aircraft, including a battery holder for accommodating at least one battery, a connection for establishing electrical contact between the at least one battery and an electrical drive of the aircraft, and a primary securing device for locking the at least one battery in the battery holder. The important factor is that the battery holding device includes at least one secondary securing device for locking the at least one battery in the battery holder, wherein the secondary securing device can be closed and released independently of the primary securing device. The invention also relates to a battery system, to an aircraft and to a corresponding method.

Claims

1. A battery holding device for an electrically driven aircraft, comprising: a battery holder for accommodating at least one battery; a connection for establishing electrical contact between the at least one battery and an electrical drive of the aircraft; a primary securing device for locking the at least one battery in the battery holder; and at least one secondary securing device for locking the at least one battery in the battery holder, wherein the secondary securing device is closeable and releasable independently of the primary securing device.

2. The battery holding device as claimed in claim 1, wherein the at least one secondary securing device comprises at least one of a mechanical latch, a form fit, at least one hook, or at least one clip.

3. The battery holding device as claimed in claim 1, wherein the at least one secondary securing device is configured such that a connection for establishing electrical contact between the at least one battery and a drive of the aircraft is establishable only in a closed state of the secondary securing device.

4. The battery holding device as claimed in claim 1, wherein the at least one secondary securing device is configured such that the secondary securing device blocks a connection for establishing electrical contact between the at least one battery and a drive of the aircraft in an open state.

5. The battery holding device as claimed in claim 4, wherein the connection for establishing electrical contact includes a plurality of plug connectors and the secondary securing device blocks at least one plug connector grommet in the open state.

6. The battery holding device as claimed in claim 1, wherein the primary securing device comprises an automatic locking system, and the at least one secondary securing device comprises a locking system that requires active actuation.

7. A battery system for an electrically driven aircraft, comprising at least one battery holding device as claimed in claim 1 and at least one battery.

8. A vertical take-off and landing aircraft comprising at least one battery holding device as claimed in claim 1 for at least one replaceable battery.

9. A method for locking at least one battery in a battery holding device of an electrically driven aircraft, the method comprising: A) inserting the at least one battery into a battery holder of the battery holding device, B) locking the at least one battery in the battery holder by a primary securing device, and C) additionally locking the at least one battery in the battery holder of the battery holding device by at least one secondary securing device.

10. A method for changing a battery in a battery holding device of an electrically driven aircraft, the method comprising: A) releasing a primary securing device of the at least one battery in the battery holder, B) removing the battery from the battery holder, C) inserting at least one new battery into the battery holding device, D) locking the at least one new battery in the battery holder by the primary securing device, wherein at least one secondary securing device is additionally provided and the method further comprises releasing the secondary securing device in a method step 0 before method step B, and locking the at least one new battery in the battery holder in a method step E after method step C by the at least one secondary securing device.

11. The method as claimed in claim 9, further comprising: before inserting the at least one battery into the battery holder, raising the aircraft at lifting points to such an extent that spring elements of the aircraft are in an unloaded state.

12. The method as claimed in 9, further comprising upon the closing of the secondary securing device, providing feedback relating to correct locking of the secondary securing device.

13. The method as claimed in claim 12, wherein the feedback comprises at least one of visual feedback, a colored marking, electronic feedback, or acoustic feedback.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0061] Further preferred features and embodiments of the battery holding device according to the invention and of the method according to the invention are explained below on the basis of exemplary embodiments and the figures, in which:

[0062] FIGS. 1A-1C show a schematic illustration of an exemplary embodiment according to the invention;

[0063] FIG. 2 shows a schematic illustration of an exemplary embodiment according to the invention with open secondary securing device;

[0064] FIG. 3 shows a schematic illustration of an exemplary embodiment with closed secondary securing device.

DETAILED DESCRIPTION

[0065] In FIGS. 1A-1C, 2, and 3, identical reference signs denote identical or identically acting elements.

[0066] FIG. 1A shows a schematic illustration of a section of an aircraft, the battery holding device in the present case. The battery 2, a battery assembly with nine batteries in the present case, is inserted into the battery holding device 1.

[0067] Plug connections 3a, 3b for establishing an electrical connection between the battery 2 and the drive of the aircraft are provided on the battery holding device 1. The plug connector grommets 3a are arranged on the battery holding device 1. The complementary plug connections for plugging in the plug connector grommets 3a are provided on the battery 2.

[0068] In the present case, the secondary securing device 5 is in the form of a clip. The secondary securing device 5 is open in the illustration in FIG. 1A.

[0069] FIG. 1B illustrates the battery 2 in the inserted state with closed primary securing device 4.

[0070] The primary securing device 4 are illustrated in detail in sub-FIG. 1C. In the present case, the primary securing device are in the form of latching hooks, as known from the prior art.

[0071] FIG. 2 shows a schematic illustration of a section of a battery holding device after method step D.

[0072] The secondary securing device 5 is open and blocks the plug connection 3a, 3b between the battery 2 and the electrical drive of the aircraft. In the present case, the secondary securing device 5 is in the form of a clip. In order to establish the connection, that is to say to make contact with the battery 2 via the plug connectors 3a, 3b, the clip 5 must be closed.

[0073] FIG. 3 shows the schematic illustration of the section from FIG. 2 with closed secondary securing device 5.

[0074] The clip 5 is closed, with the result that the battery assembly 2 is locked in the battery holder. The closed clip 5 engages with the batteries 2 by being pivoted into and engaging with a corresponding space(s) or recess(es) to hold the batteries 2 in place, and no longer blocks the plug connection between the plug connectors 3a and the battery contact device 3b. The electrical contact can therefore be established between the battery 2 and the drive of the aircraft, as indicated by the arrow.