阅读说明：本技术 具有降落伞的无人机及其控制方法 (Unmanned aerial vehicle with parachute and control method thereof ) 是由 陈英杰 王泰元 杨易达 赖俊旭 于 2020-07-06 设计创作，主要内容包括：一种具有降落伞的无人机,包括无人机主体及降落伞模块。降落伞模块包括基座、罩体、可充气材、降落伞及充气装置。基座配置于无人机主体上。罩体覆盖于基座上而在罩体与基座之间形成容纳空间。可充气材配置于基座上而收合于容纳空间内。降落伞连接于可充气材与罩体且收合于容纳空间内。充气装置配置于基座上且连接于可充气材。当充气装置对可充气材进行充气时,可充气材膨胀并撞击罩体而使罩体分离于无人机主体,以增加降落伞与无人机主体之间的距离并带动降落伞展开。此外,此无人机的控制方式亦被提及。(An unmanned aerial vehicle with a parachute comprises an unmanned aerial vehicle main body and a parachute module. The parachute module comprises a base, a cover body, an inflatable material, a parachute and an inflation device. The base disposes in the unmanned aerial vehicle main part. The cover body covers the base to form an accommodating space between the cover body and the base. The inflatable material is arranged on the base and is folded in the accommodating space. The parachute is connected with the inflatable material and the cover body and is folded in the accommodating space. The inflation device is arranged on the base and connected with the inflatable material. When aerating device aerifys inflatable material, inflatable material inflation and striking cover body and make the cover body separate in the unmanned aerial vehicle main part to increase the distance between parachute and the unmanned aerial vehicle main part and drive the parachute and expand. In addition, the control mode of the unmanned aerial vehicle is also mentioned.)

1. The utility model provides an unmanned aerial vehicle with parachute, its characterized in that, this unmanned aerial vehicle includes unmanned aerial vehicle main part and parachute module, wherein:

the parachute module includes base, the cover body, can fill material, parachute and aerating device, wherein:

the base is configured on the unmanned aerial vehicle main body;

the cover body covers the base to form an accommodating space between the cover body and the base;

the inflatable material is arranged on the base and is folded in the accommodating space;

the parachute is connected with the inflatable material and the cover body and is folded in the accommodating space; and

the inflation device is disposed on the base and connected to the inflatable material, wherein when the inflation device inflates the inflatable material, the inflatable material expands and impacts the cover body to separate the cover body from the main body of the unmanned aerial vehicle, so as to increase the distance between the parachute and the main body of the unmanned aerial vehicle and drive the parachute to unfold.

2. A drone with a parachute according to claim 1, wherein the inflatable material becomes a column after being inflated by the inflation device.

3. An unmanned aerial vehicle with a parachute according to claim 1, wherein the outer surface of the cover body is a convex arc surface.

4. A drone with a parachute according to claim 1, further comprising a first sensing module, wherein the first sensing module is configured to the drone body and configured to sense a flight status of the drone body, the parachute module configured to determine whether to control the inflation device to inflate the inflatable material in accordance with the flight status of the drone body sensed by the first sensing module.

5. The unmanned aerial vehicle with a parachute of claim 4, wherein the first sensing module comprises a first sensing element and a processing unit, the first sensing element is used for sensing the flight state of the unmanned aerial vehicle body, and the processing unit is used for judging whether to control the inflation device to inflate the inflatable material according to the flight state of the unmanned aerial vehicle body sensed by the first sensing element.

6. A drone with a parachute according to claim 5, wherein the parachute module is configured to determine whether to activate the processing unit depending on the speed of the drone body sensed by the first sensing element.

7. The unmanned aerial vehicle with a parachute of claim 1, wherein the parachute module comprises a second sensing element and a determining element, the second sensing element is used for sensing the flight state of the unmanned aerial vehicle body, and the determining element is used for determining whether to control the inflating device to inflate the inflatable material according to the flight state of the unmanned aerial vehicle body sensed by the second sensing element.

8. An unmanned aerial vehicle having a parachute as recited in claim 1, wherein the parachute module further comprises a locking assembly configured on the base and configured to lock the shroud to the base.

9. The drone with a parachute of claim 8, further comprising a first sensing module, the first sensing module comprising a first sensing element and a processing unit, the first sensing element being configured to sense a flight status of the drone body, the processing unit being configured to determine whether to control the locking assembly to release the shroud based on the flight status of the drone body sensed by the first sensing element.

10. An unmanned aerial vehicle having a parachute according to claim 8, wherein the parachute module includes a second sensing element for sensing a flight state of the unmanned aerial vehicle body and a determination element for determining whether to control the locking assembly to release the shroud body according to the flight state of the unmanned aerial vehicle body sensed by the second sensing element.

11. A method of controlling a drone with a parachute, the method comprising:

arranging a parachute module on the unmanned aerial vehicle main body, wherein the parachute module comprises an inflation device, an inflatable material, a cover body and a parachute;

inflating the inflatable material with the inflation device to expand the inflatable material; and

borrow by the inflation can the material striking the cover body so that the cover body with the parachute separate in the unmanned aerial vehicle main part, and make connect in the cover body with can the material the parachute with the distance between the unmanned aerial vehicle main part increases and drive the parachute expandes.

12. The control method according to claim 11, characterized by further comprising:

sensing the flight state of the unmanned aerial vehicle main body by means of a first sensing module of the unmanned aerial vehicle main body; and

the parachute module is used for judging whether to control the inflating device to inflate the inflatable material according to the flying state of the unmanned aerial vehicle main body sensed by the first sensing module.

13. The control method according to claim 12, characterized by further comprising:

sensing the flight state of the unmanned aerial vehicle main body by means of a first sensing element of the first sensing module; and

the processing unit of the first sensing module is used for judging whether to control the inflating device to inflate the inflatable material according to the flight state of the unmanned aerial vehicle main body sensed by the first sensing element.

14. The control method of claim 13, wherein the first sensing module determines whether to activate the processing unit according to the speed of the drone body sensed by the first sensing element.

15. The control method according to claim 12, characterized by further comprising:

sensing the flight state of the unmanned aerial vehicle main body by means of a second sensing element of the parachute module; and

and judging whether to control the inflating device to inflate the inflatable material or not by means of a judging element of the parachute module according to the flying state of the unmanned aerial vehicle main body sensed by the second sensing element.

16. The control method according to claim 15, wherein the parachute module determines whether to activate the determination element according to the speed of the drone body sensed by the second sensing element.

17. The control method according to claim 16, wherein the determining element determines whether to control the inflating device to inflate the inflatable material according to at least one of the inclination and the acceleration of the main body of the drone sensed by the second sensing element.

18. The control method of claim 12, further comprising locking the cover by a locking assembly.

19. The control method according to claim 18, characterized by further comprising:

sensing the flight state of the unmanned aerial vehicle main body by means of a first sensing element of the first sensing module; and

the processing unit of the first sensing module judges whether to control the locking component to release the cover body according to the flight state of the unmanned aerial vehicle main body sensed by the first sensing element.

20. The control method according to claim 18, characterized by further comprising:

sensing the flight state of the unmanned aerial vehicle main body by means of a second sensing element of the parachute module; and

the judging element of the parachute module judges whether to control the locking component to release the cover body according to the flying state of the unmanned aerial vehicle main body sensed by the second sensing element.

Technical Field

The present invention relates to an aircraft and a control method thereof, and more particularly, to an unmanned aerial vehicle with a parachute and a control method thereof.

Background

Unmanned aerial vehicle is a carrier that does not have the personnel of carrying. Typically using remote control, guidance systems or autonomous driving. Can be used in scientific research, site exploration, military, leisure and entertainment. The most commercialized unmanned aerial vehicles at present are unmanned aerial vehicles. The flying carrier with built-in or external camera and video camera is commonly called aerial camera. The global market for drones has grown substantially in recent years and has become an important tool for commercial, government and consumer applications. The method can support solutions in various fields, and is widely applied to the fields of buildings, petroleum, natural gas, energy, agriculture, disaster relief and the like.

In order to avoid the unmanned aerial vehicle from falling to damage or injure other people, a parachute can be configured on the unmanned aerial vehicle. However, in the process of parachute deployment, if the unmanned aerial vehicle is in a state of uncontrolled rotation or is in insufficient height, the unmanned aerial vehicle is prone to falling damage or injury to others due to the fact that the parachute is wound on the body or the unmanned aerial vehicle is not in time to deploy.

Disclosure of Invention

The invention provides an unmanned aerial vehicle with a parachute and a control method thereof, which can ensure that the parachute of the unmanned aerial vehicle is smoothly unfolded.

The unmanned aerial vehicle with the parachute comprises an unmanned aerial vehicle main body and a parachute module. The parachute module comprises a base, a cover body, an inflatable material, a parachute and an inflation device. The base disposes in the unmanned aerial vehicle main part. The cover body covers the base to form an accommodating space between the cover body and the base. The inflatable material is arranged on the base and is folded in the accommodating space. The parachute is connected with the inflatable material and the cover body and is folded in the accommodating space. The inflation device is arranged on the base and connected with the inflatable material. When aerating device aerifys inflatable material, inflatable material inflation and striking cover body and make the cover body separate in the unmanned aerial vehicle main part to increase the distance between parachute and the unmanned aerial vehicle main part and drive the parachute and expand.

The control method of the unmanned aerial vehicle comprises the following steps. Provide the parachute module in the unmanned aerial vehicle main part, wherein the parachute module includes aerating device, inflatable material, the cover body and parachute. The inflatable material is inflated by the inflating device so as to expand the inflatable material. Borrow the inflatable material striking cover body so that the cover body separates in the unmanned aerial vehicle main part by inflation, and make connect the distance increase between the cover body and the parachute of inflatable material and the unmanned aerial vehicle main part and drive the parachute and expand.

Based on the above, in the unmanned aerial vehicle of the present invention, when the parachute module starts to actuate, the inflatable material expands to drive the parachute to move so as to separate the parachute from the unmanned aerial vehicle main body by a proper distance, thereby preventing the parachute from being smoothly unfolded due to being unexpectedly wound around the unmanned aerial vehicle main body. In addition, the cover body used for accommodating the parachute and the inflatable material can move together with the parachute along with the expansion of the inflatable material in the process of actuating the parachute module so as to resist turbulent flow and have the effect of guiding the parachute to unfold. Borrow this, can ensure that unmanned aerial vehicle's parachute can play a role smoothly, and reducible parachute expandes required time completely.

Drawings

Fig. 1 is a schematic perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.

Figure 2 is a schematic view of the parachute module of figure 1.

Fig. 3 is a schematic view illustrating the parachute module of fig. 1 starting to actuate.

Figure 4 shows a schematic view of the parachute of figure 2 fully deployed.

Fig. 5 is a flowchart of a method for controlling an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 6 is a control schematic of the parachute module.

Detailed Description

The foregoing and other technical and scientific aspects, features and utilities of the present invention will be apparent from the following detailed description of various embodiments, which is to be read in connection with the accompanying drawings. Directional terms used in the following embodiments, such as "up", "down", "front", "back", "left", "right", etc., refer to directions of the drawings only. Accordingly, the directional terminology is used for purposes of illustration and is in no way limiting.

Fig. 1 is a schematic perspective view of an unmanned aerial vehicle according to an embodiment of the present invention. Figure 2 is a schematic view of the parachute module of figure 1. Referring to fig. 1 and 2, the drone 100 of the present embodiment includes a drone main body 110 and a parachute module 120. The parachute module 120 includes a base 122, a cover 124, an inflatable material 126, a parachute 128, a control unit 127, and an inflator 129. The base 122 is configured/fixed in a suitable position on the drone body 110, where the suitable position is, for example, the end of the drone body 110 away from the rotor, which can effectively avoid the drone 100 from falling down due to the winding of the rotor when the parachute is opened. The cover 124 covers the base 122 to form a receiving space S between the cover 124 and the base 122. The inflatable material 126 is disposed on the base 122 and is folded in the accommodating space S, and the parachute 128 connects the inflatable material 126 and the cover 124 and is folded in the accommodating space S. The inflator 129 is disposed on the base 122 and connected to the inflatable material 126.

Fig. 3 is a schematic view illustrating the parachute module of fig. 1 starting to actuate. Figure 4 shows a schematic view of the parachute of figure 2 fully deployed. When the parachute module 120 starts to actuate, the inflation device 129 inflates the inflatable material 126, and the inflatable material 126 expands into a column as shown in fig. 3 and hits the cover 124 to separate the cover 124 from the main drone body 110 as shown in fig. 3, so as to increase the distance between the parachute 128 and the main drone body 110 and drive the parachute 128 to unfold as shown in fig. 4. Thereby, the parachute 128 can be effectively prevented from being unintentionally wound around the drone body 110 or the rotor of the drone body 110 and not being smoothly deployed. In addition, the cover 124 for receiving the parachute 128 and the inflatable material 126 moves with the parachute 128 as the inflatable material 126 expands during the actuation of the parachute module 120 as described above. In addition, when the parachute module 120 is not actuated, the outer surface of the cover 124 is, for example, a convex arc surface, or is designed to be streamlined in conformity with the shape of the main body 110 of the drone, which has an effect of guiding the deployment direction of the parachute 128 in addition to reducing the disturbance of the airflow or the generation of turbulence when the drone 100 is flying. By this, the parachute 128 of the unmanned aerial vehicle 100 can be ensured to function smoothly, and the time required for the parachute 128 to be completely deployed can be reduced.

Fig. 1 and 3 schematically illustrate the position of the parachute module 120 on the main body 110 of the drone, and the parachute module 120 may be installed at other positions on the main body 110 of the drone, which is not limited in the present invention. For example, the parachute module 120 is disposed at the end of the main body 110 away from the rotor, so that the problem that the drone 100 falls due to the winding of the rotor when the parachute 128 is opened can be effectively avoided, or the parachute module 120 is mounted at the position close to the center of gravity of the main body 110.

In the present embodiment, the inflatable material 126 is made of a composite material with high mechanical properties, such as a woven fabric, and has sufficient strength to withstand the impact of gas during inflation. The inflatable material 126 is used to eject the parachute 128 and the cover 124 away from the drone body 110. In other embodiments, the inflatable material 126 may be made of other suitable materials, and the invention is not limited thereto. In addition, the inflation device 129 of the present embodiment is, for example, a high pressure gas cylinder or other types of devices capable of providing high pressure gas to inflate the inflatable material 126 with the high pressure gas.

The control method of the parachute module of the unmanned aerial vehicle according to the present embodiment is described below with reference to a flowchart. Fig. 5 is a flowchart of a method for controlling an unmanned aerial vehicle according to an embodiment of the present invention. Referring to fig. 5, first, the parachute module 120 is disposed on the main body 110 of the drone, wherein the parachute module 120 includes an inflator 129, an inflatable material 126, a cover 124 and a parachute 128 (step S1). Next, the inflatable material 126 is inflated by the inflator 129 to expand the inflatable material 126 (step S2). The inflated inflatable material 126 hits the cover 124 to separate the cover 124 and the parachute 128 from the main drone body 110, and the distance between the parachute 128 connected to the cover 124 and the inflatable material 126 and the main drone body 110 is increased to expand the parachute 128 (step S3).

The operation timing of the parachute module 120 will be described in detail below. The drone 100 of the present embodiment further includes a first sensing module 130 (shown in fig. 1). The first sensing module 130 includes, for example, a first sensing element 130a such as a gyroscope and/or magnetometer and a processing unit 130 b. The first sensing module 130 is disposed in the main drone body 110 and is used for sensing the speed, the acceleration, the inclination angle, and the like of the main drone body 110 to generate a sensing signal. The processing unit of the first sensing module 130 determines the current flight state of the drone 100 according to the sensing signals and generates a flight signal. By way of electrical connection, the parachute module 120 can receive the flight signal from the first sensing module 130, such that the inflation device 129 inflates the inflatable material 126 to deploy the parachute 128. In detail, the flight status of the main body 110 of the drone, such as whether the drone 100 is in flight and stalled, can be known according to the sensing signal of the first sensing module 130, and then the processing unit 130b of the first sensing module 130 determines whether to send out the flight signal to the control unit 127 of the parachute module 120 to control the inflator 129 to inflate the inflatable material 126 to deploy the parachute 128.

Referring to fig. 2 again, in the present embodiment, the parachute module 120 further includes at least one locking component 125, and the locking component 125 is disposed on the base 122 and is used for locking the cover 124 to the base 122. When the first sensing module 130 senses the flight status (e.g., at least one of the inclination angle and the acceleration) of the drone 100 and the drone 100 stalls, it sends a flight signal to the parachute module 120, controls the at least one locking component 125 to open and release the cover 124, and then controls the inflator 129 to inflate the inflatable material 126 to deploy the parachute 128. The locking component 125 is, for example, a snap device or a lock. The locking assembly 125 may lock and release the cover 124 by any suitable locking mechanism, and the invention is not limited to this specific form.

In other embodiments, the control unit included in the parachute module 120 itself may be utilized to perform the above determination and control. This will be specifically described below.

Fig. 6 is a control schematic of the parachute module. After the drone 100 takes off, the first sensing module 130 preferentially controls the operation of the parachute module 120. However, when the first sensing module 130 cannot be actuated due to some factors (for example, the first sensing element or the processing unit is damaged or loses electric drive), the control unit 127 of the parachute module 120 controls the operation inside the parachute module 120. In the parachute module 120 of the present embodiment, as shown in fig. 2 and fig. 6, the control unit 127 further includes a second sensing element 127a and a determining element 127 b. The second sensing elements 127a may include gyroscopes and/or magnetometers for sensing flight conditions of the drone body 110, such as velocity, acceleration and inclination. The determining element 127b is used for knowing whether the drone 100 is in flight or stalled according to the sensing signal of the flying state of the drone main body 110 sensed by the second sensing element 127a, and determining whether the inflation device 129 needs to be controlled to inflate the inflatable material 126 to deploy the parachute 128 according to the sensing signal.

In other words, in the case that the first sensing module 130 (shown in fig. 1) and the second control unit 127 (shown in fig. 6) are provided at the same time, the flying state sensed by the first sensing module 130 can be preferentially used as the basis for determining whether to start the parachute module 120. In addition, the second sensing element 127a and the determining element 127b of the second control unit 127 can be used as a backup, and can be replaced when the first sensing module 130 of the main body 110 of the drone and the determining mechanism thereof are turned off or fail.

In an embodiment, the parachute module 120 may first know whether the drone 100 is flying according to the speed of the drone body 110 sensed by the first sensing element 130a, and accordingly determine whether to start the processing unit 130 b. If the first sensing element 130a senses that the speed of the main body 110 of the drone is lower than the predetermined value, it indicates that the drone 100 has not taken off, and the processing unit 130b is not activated. In another embodiment, if the first sensing element 130a fails, the parachute module 120 can first know whether the drone 100 is flying according to the speed of the drone main body 110 sensed by the second sensing element 127a, and accordingly determine whether to start the determining element 127 b. If the second sensing element 127a senses that the speed of the main body 110 of the drone is lower than the predetermined value, it indicates that the drone 100 has not taken off, and the determining element 127b is not activated at this time. Therefore, the processing unit 130b or the determining element 127b can be prevented from mistakenly triggering the actuation of the parachute module 120 when the unmanned aerial vehicle 100 does not take off yet. If the first sensing element 130a senses that the speed of the main body 110 of the drone is higher than the predetermined value, it indicates that the drone 100 is flying, and the processing unit 130b is activated. If the first sensing element 130a fails, the second sensing element 127a senses that the speed of the main body 110 of the drone is higher than a predetermined value, which indicates that the drone 100 is flying, and the determining element 127b is activated.

After the processing unit 130b is activated, it can know whether the drone 100 stalls according to at least one of the inclination angle and the acceleration of the drone main body 110 sensed by the first sensing element 130a, so as to determine whether to control the inflation device 129 to inflate the inflatable material 126 to deploy the parachute 128. If the first sensing element 130a fails, the determining element 127b can determine whether the drone 100 stalls according to at least one of the inclination and the acceleration of the drone body 110 sensed by the second sensing element 127a after being activated, so as to determine whether to control the inflation device 129 to inflate the inflatable material 126. If the drone 100 has stalled, the inflation device 129 is controlled to inflate the inflatable material 126 to deploy the parachute 128.

Referring to fig. 2 and 6, the determining element 127b can determine whether the drone 100 stalls according to the flight status (e.g., at least one of the inclination and the acceleration) of the drone body sensed by the second sensing element 127a, so as to determine whether to control the locking component 125 to release the cover 124. If the drone 100 has stalled, the locking assembly 125 is controlled to release the cover 124 and then the inflation device 129 is controlled to inflate the inflatable material 126 as described above to deploy the parachute 128. The locking assembly 125 may lock and release the cover 124 by any suitable locking mechanism, and the invention is not limited to this specific form.

The processing unit 130b and the determining element 127b are, for example, a Central Processing Unit (CPU), or other Programmable general purpose or special purpose microprocessors (microprocessors), Digital Signal Processors (DSPs), Programmable controllers, Application Specific Integrated Circuits (ASICs), Programmable Logic Devices (PLDs), or other similar devices or chips of combinations thereof.

In summary, in the unmanned aerial vehicle of the present invention, when the parachute module starts to actuate, the inflatable material expands to drive the parachute to eject so that the parachute is separated from the main body of the unmanned aerial vehicle by a suitable distance, thereby preventing the parachute from being unintentionally wound around the main body or the rotor of the unmanned aerial vehicle and being unable to be smoothly deployed. In addition, the cover body used for accommodating the parachute and the inflatable material can move together with the parachute along with the expansion of the inflatable material in the process of actuating the parachute module, and the parachute is guided to be unfolded. Borrow this, can ensure that unmanned aerial vehicle's parachute can play a role smoothly, and reducible parachute expandes required time completely.

However, the above description is only a preferred embodiment of the present invention, and the scope of the present invention should not be limited thereby, and all the simple equivalent changes and modifications made by the claims and the summary of the invention are still within the scope of the present invention. Moreover, not all objects, advantages, or features disclosed herein are to be achieved in any one embodiment or claim of the present invention. In addition, the abstract and the title of the invention are provided for assisting the patent search and are not intended to limit the scope of the invention. Furthermore, the terms "first", "second", and the like in the description or the claims are used only for naming elements (elements) or distinguishing different embodiments or ranges, and are not used for limiting the upper limit or the lower limit on the number of elements.

Description of reference numerals:

100 unmanned plane

110 unmanned aerial vehicle main body

120 parachute module

122 base

124, cover body

125 locking assembly

126 inflatable material

127 control unit

127a second sensing element

127b judging element

128: parachute

129 air charging device

130 first sensing module

130a first sensing element

130b processing unit

S, containing space

S1-S3.