WO2018188054A1 - Fuel tank separate-dropping system for unmanned aerial vehicle - Google Patents
Fuel tank separate-dropping system for unmanned aerial vehicle Download PDFInfo
- Publication number
- WO2018188054A1 WO2018188054A1 PCT/CN2017/080531 CN2017080531W WO2018188054A1 WO 2018188054 A1 WO2018188054 A1 WO 2018188054A1 CN 2017080531 W CN2017080531 W CN 2017080531W WO 2018188054 A1 WO2018188054 A1 WO 2018188054A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- fuel tank
- tank
- axe
- steel sheet
- clockwork
- Prior art date
Links
- 239000002828 fuel tank Substances 0.000 title claims abstract description 30
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 37
- 239000010959 steel Substances 0.000 claims abstract description 37
- 238000005498 polishing Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
- B64D37/12—Constructional adaptations thereof jettisonable
Definitions
- the present invention relates to a drone aircraft fuel tank dispensing system.
- the UAV aircraft sub-tank refers to a fuel tank that is hung in the middle of the fuselage or under the wing and has a streamlined, two-pointed tip.
- Hanging the auxiliary fuel tank can increase the range and duration of the aircraft, and the aircraft can throw away the auxiliary fuel tank when necessary in air combat, and put the battle into better combat with better maneuverability.
- the auxiliary tank shape that can be discarded in the auxiliary tank is completely different from the subsequent streamlined design. In order to match the curve of the installation part body, it is necessary to specially design the aircraft.
- ⁇ needs to be fixed at the place below the fuselage, which has a great impact on the performance of the aircraft, and even an uncontrollable situation, which is hardly used in combat missions and is only used for transport flights.
- some of the streamlined auxiliary fuel tanks used by some aircraft could not be discarded after they were needed. Due to the impact on the performance of the aircraft, the disposable fuel tanks almost completely replaced this type of use later.
- Some aircraft entering the jet generation will be equipped with non-disposable auxiliary fuel tanks at both ends of the wing. This type of auxiliary tank has the ability to suppress the vibration or distortion of the wing structure.
- the models used include the T-33 trainer, the F-5A/B fighter, and the 300-gallon auxiliary tank of the B-25 bomber under the wing. and many more. Only a very small number of models will have a sub-tank in the fuselage. At present, only the Russian Su-27 fighter is designed to claim that the sub-tank is in the fuselage.
- a drone aircraft fuel tank dispensing system is provided.
- a UAV aircraft fuel tank sub-distribution system the main structures thereof are: a base plate, a bottom plate groove, a guide rail rod, a fuel tank tray, an axe shape a steel sheet, an auxiliary steel sheet, a reservoir chamber, a reservoir tank, a barrel, an arc groove a, an arc groove b, a connecting rod a, a pin rod, and a connecting rod b, wherein the base plate is provided with a storage In the oil tank chamber, one end of the oil storage tank cavity penetrates the oil storage tank groove; the arc groove piece a and the arc groove piece b are respectively welded with a rail rod; and the oil rod body tray is welded on the rail rod.
- the eccentric position of the axe steel sheet is fixed with a barrel, the barrel distributing strip and the disc body; the oil tank tray and the barrel are connected by a connecting rod b
- the axe steel piece and the auxiliary steel piece are respectively fixed through the pin rod; the connecting rod a is drawn between the pin rod and the barrel.
- the disc body of the clockwork disc is stuck outside the arc groove piece & the arc groove piece b; the bottom plate of the base plate has a bottom plate groove, and the bottom plate groove is matched with the position of the axe steel piece.
- the oil tank body can be clamped in the oil storage tank tank tank.
- the specific eccentric point position length of the axe steel piece is a length at which the center of the distance is equal to the maximum diameter of the oil tank body.
- the structure is simple, and the components are clearly structured; the design can only produce one fuel tank at a time, so that an effective load card accident can occur.
- FIG. 1 is a structural diagram of an overall oil tank of a submarine aircraft fuel tank splitting and polishing system according to the present invention.
- 2 is a structural diagram of an overall oil-free tank of a submarine aircraft fuel tank sub-polishing system according to the present invention.
- Fig. 3 is a structural diagram showing the movement of a submersible aircraft fuel tank sub-polishing system according to the present invention.
- Fig. 4 is a structural view showing the base portion of a submersible aircraft fuel tank splitting system of the present invention.
- An unmanned aerial vehicle fuel tank splitting and polishing system the main structures thereof are: a base plate 1, a floor plate 2, a rail rod 3, a tank body tray 4, an axe steel sheet 5, an auxiliary steel sheet 6, a storage tank a chamber 7, a reservoir tank 8, a barrel 9, an arc slot a0, an arc slot bl l, a link al2, a pin rod 13, a link bl4, and the base plate 1 is provided with a reservoir chamber 7
- the oil storage tank cavity 7 is connected through the oil storage tank groove 8; the arc groove piece a0 and the arc groove piece M l are respectively welded with the guide rod 3; the rail rod 3 is welded with the oil tank body tray 4.
- the eccentricity of the axe steel sheet 5 A barrel 9 is fixed at a position, the barrel 9 is distributed with two parts of the disc body; the oil tank tray 4 and the barrel 9 are linked by a connecting rod M4; The steel piece 5 and the auxiliary steel piece 6 are penetrated and fixed by the pin rod 13; the connecting rod a1 is pulled between the pin rod 13 and the barrel 9.
- the disc body of the barrel 9 is clamped on the arc slot a10 and the arc slot bl l; the base plate 1 has a bottom slot 2, a bottom slot 2 and an axe steel 5 Match.
- the oil tank body 8 can hold the oil tank body.
- the specific eccentric point position length of the axe steel sheet 5 is the length at which the center of the circle is equal to the maximum diameter of the oil tank body.
- the working principle of the invention By manually sliding the rail rod 3 from top to bottom, a fuel tank can be dropped out; the specific realization process is to take the oil tank body of the tank body tray 4 last time, and then pull the rail rod 3 Back to the 90 degree vertical direction, during the retraction process, since the clockwork disc 9 is disposed at the eccentric position of the axe steel sheet 5, when the axe steel sheet 5 is rotated in the vertical direction of the rail by the rail rod 3, the axe shape The edge position of the steel sheet 5 and the auxiliary steel sheet 6 will shrink downward. When completely vertical, the oil tank body in the reservoir chamber 7 falls out of a fuel tank and rests on the side of the axe steel sheet 5 and the auxiliary steel sheet 6. Then, the rail rod 3 is turned back to the horizontal position.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Rigid Or Semi-Rigid Containers (AREA)
Abstract
A fuel tank separate-dropping system for an unmanned aerial vehicle. A fuel tank storage chamber (7) is provided on a base bottom plate (1); and one end of the fuel tank storage chamber (7) is communicated with a fuel tank storage groove (8); guide rail rods (3) are respectively welded on an arc slotted sheet a (10) and an arc slotted sheet b (11); a fuel tank tray (4) is welded on the guide rail rods (3); a clockwork plate (9) is fixed at a center position of an axe-shaped steel sheet (5); the clockwork plate (9) is divided into two parts, i.e., a clockwork component and a disc body; the fuel tank tray (4) and the clockwork plate (9) are linked by a connecting rod b (14); the axe-shaped steel sheet (5) and an auxiliary steel sheet (6) are penetrated and fixed by a pin rod (13); a connecting rod a (12) is connected between the pin rod (13) and the clockwork plate (9); the disk body of the clockwork plate (9) is limited at the outer side of the arc slotted sheet a (10) and the arc slotted sheet b (11); a bottom plate groove (2) is formed on the base bottom plate (1); and the bottom plate groove (2) matches the axe-shaped steel sheet (5) in position. The system has a simple structure, the constitution of each component is clear; only one fuel tank can be dropped by one pull.
Description
一种无人机飞行器油箱分抛系统 Unmanned aerial vehicle fuel tank splitting system
技术领域 Technical field
[0001] 本发明涉及一种无人机飞行器油箱分抛系统。 [0001] The present invention relates to a drone aircraft fuel tank dispensing system.
背景技术 Background technique
[0002] 无人机飞行器副油箱是指挂在机身或机翼下面的中间粗、 两头尖呈流线型的燃 油箱。 挂副油箱可以增加飞机的航程和续航吋间， 而飞机在空战在必要的吋候 又可以扔掉副油箱， 以较好的机动性投入战斗。 副油箱可抛弃的副油箱外型与 后来的流线形设计完全不同， 为了配合安装部位机身的曲线， 需要特别为使用 的飞机设计。 使用吋需要固定在机身下方预定处， 对于飞机的性能影响很大， 甚至会出现难以控制的情况， 几乎不使用于作战任务中， 仅用于运输飞行上。 第二次世界大战初期有部分飞机使用的流线形副油箱无法在需要吋加以抛弃， 由于对飞机的性能也有影响， 可抛弃的副油箱稍后几乎全部取代这一类的使用 。 进入喷射机吋代的部分飞机在机翼两端会加装不可抛弃的副油箱。 这一类副 油箱同吋具有抑制机翼结构震动或者是扭曲的情形， 使用的机种包过 T-33教练机 、 F-5A/B战斗机， 以及部分 B-25轰炸机在机翼下的 300加仑副油箱等等。 只有非 常少数的机种会在机身内设置副油箱， 目前仅有俄罗斯的 Su-27战斗机在设计上 宣称副油箱是在机身当中。 [0002] The UAV aircraft sub-tank refers to a fuel tank that is hung in the middle of the fuselage or under the wing and has a streamlined, two-pointed tip. Hanging the auxiliary fuel tank can increase the range and duration of the aircraft, and the aircraft can throw away the auxiliary fuel tank when necessary in air combat, and put the battle into better combat with better maneuverability. The auxiliary tank shape that can be discarded in the auxiliary tank is completely different from the subsequent streamlined design. In order to match the curve of the installation part body, it is necessary to specially design the aircraft. The use of 吋 needs to be fixed at the place below the fuselage, which has a great impact on the performance of the aircraft, and even an uncontrollable situation, which is hardly used in combat missions and is only used for transport flights. At the beginning of the Second World War, some of the streamlined auxiliary fuel tanks used by some aircraft could not be discarded after they were needed. Due to the impact on the performance of the aircraft, the disposable fuel tanks almost completely replaced this type of use later. Some aircraft entering the jet generation will be equipped with non-disposable auxiliary fuel tanks at both ends of the wing. This type of auxiliary tank has the ability to suppress the vibration or distortion of the wing structure. The models used include the T-33 trainer, the F-5A/B fighter, and the 300-gallon auxiliary tank of the B-25 bomber under the wing. and many more. Only a very small number of models will have a sub-tank in the fuselage. At present, only the Russian Su-27 fighter is designed to claim that the sub-tank is in the fuselage.
技术问题 technical problem
[0003] 提供一种无人机飞行器油箱分抛系统。 [0003] A drone aircraft fuel tank dispensing system is provided.
问题的解决方案 Problem solution
技术解决方案 Technical solution
[0004] 本发明解决其上述的技术问题所采用以下的技术方案： 一种无人机飞行器油箱 分抛系统， 其主要构造有： 基座底板、 底板槽、 导轨杆、 油箱体托盘、 斧形钢 片、 辅助钢片、 储油箱腔、 储油箱槽、 发条盘、 弧槽片 a、 弧槽片 b、 连杆 a、 销 钉杆、 连杆 b， 所述的基座底板上设有储油箱腔， 储油箱腔一端贯通有储油箱槽 ； 所述的弧槽片 a、 弧槽片 b上分别焊接有导轨杆； 导轨杆上焊接有油箱体托盘。
所述的斧形钢片的偏心位置处固定有发条盘， 所述的发条盘分发条和盘体两个 部分； 所述的油箱体托盘与发条盘之间通过连杆 b相联动； 所述的斧形钢片、 辅 助钢片两者之间通过销钉杆相贯穿固定； 销钉杆与发条盘之间拉结有连杆 a。 所 述的发条盘的盘体卡于弧槽片&、 弧槽片 b外； 所述的基座底板一处幵有底板槽， 底板槽与斧形钢片位置上相匹配。 进一步地， 所述的储油箱槽内可夹持油箱体 。 进一步地， 所述的斧形钢片的具体偏心点位置长度为距离圆心等于油箱体最 大直径处的长度。 [0004] The present invention solves the above technical problems and adopts the following technical solutions: A UAV aircraft fuel tank sub-distribution system, the main structures thereof are: a base plate, a bottom plate groove, a guide rail rod, a fuel tank tray, an axe shape a steel sheet, an auxiliary steel sheet, a reservoir chamber, a reservoir tank, a barrel, an arc groove a, an arc groove b, a connecting rod a, a pin rod, and a connecting rod b, wherein the base plate is provided with a storage In the oil tank chamber, one end of the oil storage tank cavity penetrates the oil storage tank groove; the arc groove piece a and the arc groove piece b are respectively welded with a rail rod; and the oil rod body tray is welded on the rail rod. The eccentric position of the axe steel sheet is fixed with a barrel, the barrel distributing strip and the disc body; the oil tank tray and the barrel are connected by a connecting rod b The axe steel piece and the auxiliary steel piece are respectively fixed through the pin rod; the connecting rod a is drawn between the pin rod and the barrel. The disc body of the clockwork disc is stuck outside the arc groove piece & the arc groove piece b; the bottom plate of the base plate has a bottom plate groove, and the bottom plate groove is matched with the position of the axe steel piece. Further, the oil tank body can be clamped in the oil storage tank tank. Further, the specific eccentric point position length of the axe steel piece is a length at which the center of the distance is equal to the maximum diameter of the oil tank body.
发明的有益效果 Advantageous effects of the invention
有益效果 Beneficial effect
[0005] 结构简单、 各个组件构成清晰； 适本设计一次扳动只能出一油箱， 因此能够很 有效的负重卡箱事故发生。 [0005] The structure is simple, and the components are clearly structured; the design can only produce one fuel tank at a time, so that an effective load card accident can occur.
对附图的简要说明 Brief description of the drawing
附图说明 DRAWINGS
[0006] 图 1为本发明一种无人机飞行器油箱分抛系统整体装油箱结构图。 图 2为本发明 一种无人机飞行器油箱分抛系统整体无油箱结构图。 图 3为本发明一种无人机飞 行器油箱分抛系统运动部分结构图。 图 4为本发明一种无人机飞行器油箱分抛系 统基座部分结构图。 图中 1-基座底板， 2-底板槽， 3-导轨杆， 4-油箱体托盘， 5- 斧形钢片， 6-辅助钢片， 7-储油箱腔， 8-储油箱槽， 9-发条盘， 10-弧槽片 a， 11- 弧槽片 b， 12-连杆 a， 13-销钉杆 a， 14-连杆 b。 1 is a structural diagram of an overall oil tank of a submarine aircraft fuel tank splitting and polishing system according to the present invention. 2 is a structural diagram of an overall oil-free tank of a submarine aircraft fuel tank sub-polishing system according to the present invention. Fig. 3 is a structural diagram showing the movement of a submersible aircraft fuel tank sub-polishing system according to the present invention. Fig. 4 is a structural view showing the base portion of a submersible aircraft fuel tank splitting system of the present invention. In the figure - 1 base plate, 2 bottom plate groove, 3-rail rod, 4-tank body tray, 5-axe steel sheet, 6-auxiliary steel sheet, 7-reservoir chamber, 8-tank tank, 9 - clockwork disc, 10-arc slot a, 11-arc slot b, 12-link a, 13-pin bar a, 14-link b.
本发明的实施方式 Embodiments of the invention
[0007] 下面结合附图 1-4对本发明的具体实施方式做一个详细的说明。 实施例: 一种 无人机飞行器油箱分抛系统， 其主要构造有： 基座底板 1、 底板槽 2、 导轨杆 3、 油箱体托盘 4、 斧形钢片 5、 辅助钢片 6、 储油箱腔 7、 储油箱槽 8、 发条盘 9、 弧 槽片 al0、 弧槽片 bl l、 连杆 al2、 销钉杆 13、 连杆 bl4， 所述的基座底板 1上设有 储油箱腔 7， 储油箱腔 7—端贯通有储油箱槽 8 ; 所述的弧槽片 al0、 弧槽片 M l上 分别焊接有导轨杆 3 ; 导轨杆 3上焊接有油箱体托盘 4。 所述的斧形钢片 5的偏心
位置处固定有发条盘 9， 所述的发条盘 9分发条和盘体两个部分； 所述的油箱体 托盘 4与发条盘 9之间通过连杆 M4相联动； 所述的斧形钢片 5、 辅助钢片 6两者之 间通过销钉杆 13相贯穿固定； 销钉杆 13与发条盘 9之间拉结有连杆 al2。 所述的发 条盘 9的盘体卡于弧槽片 alO、 弧槽片 bl l外； 所述的基座底板 1一处幵有底板槽 2 ， 底板槽 2与斧形钢片 5位置上相匹配。 所述的储油箱槽 8内可夹持油箱体。 所述 的斧形钢片 5的具体偏心点位置长度为距离圆心等于油箱体最大直径处的长度。 本发明的工作原理： 通过手动的从上往下拨动导轨杆 3， 可以掉出一个油箱； 具 体的实现过程是， 取走上一次在油箱体托盘 4的油箱体， 然后将导轨杆 3扳回 90 度垂直方向， 在扳回过程中， 由于发条盘 9设置于斧形钢片 5的偏心位置处， 当 斧形钢片 5随着导轨杆 3向 90度垂直方向转动吋， 斧形钢片 5、 辅助钢片 6的边位 置会向下的收缩， 当完全垂直吋， 储油箱腔 7内的油箱体掉出一油箱， 搁置在斧 形钢片 5、 辅助钢片 6的边上， 然后再将导轨杆 3回拨到水平位置， 在回拨的过程 中， 由于重力原因料油箱体会通过斧形钢片 5、 辅助钢片 6滑入油箱体托盘 4上； 与此同吋， 斧形钢片 5、 辅助钢片 6在储油箱腔 7处位置上又会升高， 进行限位， 防止油箱体的自动掉出。 以上显示和描述了本发明的基本原理、 主要特征和本 发明的优点。 本行业的技术人员应该了解， 本发明不受上述实施例的限制， 上 述实施例和说明书中描述的只是说明本发明的原理， 在不脱离本发明精神和范 围的前提下， 本发明还会有各种变化和改进， 这些变化和改进都落入要求保护 的本发明范围内。 本发明要求保护范围由所附的权利要求书及其等效物界定。
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A specific embodiment of the present invention will be described in detail below with reference to FIGS. Embodiments: An unmanned aerial vehicle fuel tank splitting and polishing system, the main structures thereof are: a base plate 1, a floor plate 2, a rail rod 3, a tank body tray 4, an axe steel sheet 5, an auxiliary steel sheet 6, a storage tank a chamber 7, a reservoir tank 8, a barrel 9, an arc slot a0, an arc slot bl l, a link al2, a pin rod 13, a link bl4, and the base plate 1 is provided with a reservoir chamber 7 The oil storage tank cavity 7 is connected through the oil storage tank groove 8; the arc groove piece a0 and the arc groove piece M l are respectively welded with the guide rod 3; the rail rod 3 is welded with the oil tank body tray 4. The eccentricity of the axe steel sheet 5 A barrel 9 is fixed at a position, the barrel 9 is distributed with two parts of the disc body; the oil tank tray 4 and the barrel 9 are linked by a connecting rod M4; The steel piece 5 and the auxiliary steel piece 6 are penetrated and fixed by the pin rod 13; the connecting rod a1 is pulled between the pin rod 13 and the barrel 9. The disc body of the barrel 9 is clamped on the arc slot a10 and the arc slot bl l; the base plate 1 has a bottom slot 2, a bottom slot 2 and an axe steel 5 Match. The oil tank body 8 can hold the oil tank body. The specific eccentric point position length of the axe steel sheet 5 is the length at which the center of the circle is equal to the maximum diameter of the oil tank body. The working principle of the invention: By manually sliding the rail rod 3 from top to bottom, a fuel tank can be dropped out; the specific realization process is to take the oil tank body of the tank body tray 4 last time, and then pull the rail rod 3 Back to the 90 degree vertical direction, during the retraction process, since the clockwork disc 9 is disposed at the eccentric position of the axe steel sheet 5, when the axe steel sheet 5 is rotated in the vertical direction of the rail by the rail rod 3, the axe shape The edge position of the steel sheet 5 and the auxiliary steel sheet 6 will shrink downward. When completely vertical, the oil tank body in the reservoir chamber 7 falls out of a fuel tank and rests on the side of the axe steel sheet 5 and the auxiliary steel sheet 6. Then, the rail rod 3 is turned back to the horizontal position. During the returning process, the oil tank body slides through the axe steel sheet 5 and the auxiliary steel sheet 6 into the tank body tray 4 due to gravity; The axe steel piece 5 and the auxiliary steel piece 6 are raised again at the position of the oil storage tank chamber 7, and the limit is made to prevent the oil tank body from falling out automatically. The basic principles, main features and advantages of the present invention are shown and described above. It should be understood by those skilled in the art that the present invention is not limited by the foregoing embodiments, and that the present invention is only described in the foregoing embodiments and the description of the present invention, without departing from the spirit and scope of the invention. Various changes and modifications are intended to fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and their equivalents.
Claims
[权利要求 1] 一种无人机飞行器油箱分抛系统， 其主要构造有： 基座底板 （1) 、 底板槽 （2) 、 导轨杆 （3) 、 油箱体托盘 （4) 、 斧形钢片 （5) 、 辅 助钢片 （6) 、 储油箱腔 （7) 、 储油箱槽 （8) 、 发条盘 （9) 、 弧槽 片 a ( 10) 、 弧槽片 b ( 11) 、 连杆 a ( 12) 、 销钉杆 （13) 、 连杆 b ( 14) ， 其特征在于： 基座底板 （1) 上设有储油箱腔 （7) ， 储油箱腔 (7) 一端贯通有储油箱槽 （8) ； 所述的弧槽片 a ( 10) 、 弧槽片 b ( 11) 上分别焊接有导轨杆 （3) ； 导轨杆 （3) 上焊接有油箱体托盘 ( 4) 。 所述的斧形钢片 （5) 的圆心位置处固定有发条盘 （9) ， 所述 的发条盘 （9) 分发条和盘体两个部分； 所述的油箱体托盘 （4) 与发 条盘 （9) 之间通过连杆 b ( 14) 相联动； 所述的斧形钢片 （5) 、 辅 助钢片 （6) 两者之间通过销钉杆 （13) 相贯穿固定； 销钉杆 （13) 与发条盘 （9) 之间拉结有连杆 a ( 12) 。 所述的发条盘 （9) 的盘体 卡于弧槽片 a ( 10) 、 弧槽片 b ( 11) 外； 所述的基座底板 （1) 一处 幵有底板槽 （2) ， 底板槽 （2) 与斧形钢片 （5) 位置上相匹配。 [Claim 1] A UAV aircraft fuel tank sub-distribution system, the main structures of which are: a base plate (1), a bottom plate groove (2), a rail rod (3), a tank body tray (4), an axe steel Sheet (5), auxiliary steel sheet (6), oil tank chamber (7), oil tank tank (8), clockwork disc (9), arc groove piece a (10), arc groove piece b (11), connection The rod a (12), the pin rod (13) and the connecting rod b (14) are characterized in that: the base plate (1) is provided with a reservoir chamber (7), and one end of the reservoir chamber (7) is connected with a reservoir The groove (8); the arc groove piece a (10) and the arc groove piece b (11) are respectively welded with a rail rod (3); the rail rod (3) is welded with a tank body tray (4). The clockwork disc (9) is fixed at the center of the axe steel sheet (5), the barrel (9) is distributed with the strip and the disc body; the oil tank tray (4) Between the clockwork disc (9) and the connecting rod b (14); the axe steel piece (5) and the auxiliary steel piece (6) are penetrated and fixed by the pin rod (13); A connecting rod a (12) is pulled between the pin bar (13) and the barrel (9). The disc body of the barrel (9) is stuck outside the arc groove piece a (10) and the arc groove piece b (11); the base plate (1) has a bottom plate groove (2) at one place. The bottom plate groove (2) matches the position of the axe steel piece (5).
[权利要求 2] 根据权利要求 1所述的一种无人机飞行器油箱分抛系统， 其特征在于 所述的储油箱槽 （8) 内可夹持油箱体。 [Claim 2] A UAV aircraft fuel tank dispensing system according to claim 1, wherein the oil tank tank (8) can hold the oil tank body.
[权利要求 3] 根据权利要求 1所述的一种无人机飞行器油箱分抛系统， 其特征在于 所述的斧形钢片 （5) 的具体偏心点位置长度为距离圆心等于油箱体 最大直径处的长度。
[Claim 3] The unmanned aerial vehicle fuel tank sub-polishing system according to claim 1, wherein the specific eccentric point position length of the axe steel sheet (5) is equal to the center of the tank equal to the maximum diameter of the oil tank body. The length of the place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/080531 WO2018188054A1 (en) | 2017-04-14 | 2017-04-14 | Fuel tank separate-dropping system for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/080531 WO2018188054A1 (en) | 2017-04-14 | 2017-04-14 | Fuel tank separate-dropping system for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2018188054A1 true WO2018188054A1 (en) | 2018-10-18 |
Family
ID=63792154
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CN2017/080531 WO2018188054A1 (en) | 2017-04-14 | 2017-04-14 | Fuel tank separate-dropping system for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2018188054A1 (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080173763A1 (en) * | 2007-01-19 | 2008-07-24 | Sikorsky Aircraft Corporation | Fuel jettison system |
| WO2010086677A1 (en) * | 2009-01-28 | 2010-08-05 | Jose Andres Quesada Arathoon | Ejectable tanks for aircraft |
| CN103209894A (en) * | 2010-07-28 | 2013-07-17 | 空中客车运作有限责任公司 | Hydrogen tank for h2-injection |
| CN104507811A (en) * | 2012-07-31 | 2015-04-08 | 伊顿有限公司 | Valve for jettisonable aircraft fuel tank |
| EP3075657A1 (en) * | 2015-03-31 | 2016-10-05 | Airbus Defence and Space GmbH | Multifunction pod for an aircraft |
-
2017
- 2017-04-14 WO PCT/CN2017/080531 patent/WO2018188054A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080173763A1 (en) * | 2007-01-19 | 2008-07-24 | Sikorsky Aircraft Corporation | Fuel jettison system |
| WO2010086677A1 (en) * | 2009-01-28 | 2010-08-05 | Jose Andres Quesada Arathoon | Ejectable tanks for aircraft |
| CN103209894A (en) * | 2010-07-28 | 2013-07-17 | 空中客车运作有限责任公司 | Hydrogen tank for h2-injection |
| CN104507811A (en) * | 2012-07-31 | 2015-04-08 | 伊顿有限公司 | Valve for jettisonable aircraft fuel tank |
| EP3075657A1 (en) * | 2015-03-31 | 2016-10-05 | Airbus Defence and Space GmbH | Multifunction pod for an aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203793657U (en) | Take-off assisting device for fixed-wing unmanned aerial vehicle | |
| CN100586797C (en) | Small-sized unmanned aerial vehicle rotating ejector rack | |
| CN106741948B (en) | It is a kind of to carry the unmanned plane for launching object | |
| CN103587686A (en) | Catapulted folding wing flying robot | |
| CN207274985U (en) | There is the unmanned plane that ejection is jettisoninged | |
| JP6980968B2 (en) | Agricultural unmanned machine | |
| CN107776892B (en) | Light-duty collapsible scouting and beating integrative unmanned aerial vehicle | |
| CN108408076A (en) | A kind of unmanned plane is fixed with booster rocket and is oriented to separating mechanism | |
| GB2434783A (en) | Aircraft with folded wings | |
| CN103101621A (en) | Parafoil aircraft applicable to cylindrical space loading | |
| CN111891376A (en) | Auxiliary take-off equipment for fixed-wing unmanned aerial vehicle | |
| CN105599917B (en) | A kind of unmanned plane that launches drags load dolly | |
| WO2018188054A1 (en) | Fuel tank separate-dropping system for unmanned aerial vehicle | |
| CN108069038A (en) | A kind of airborne tri-coupling type mixing suspension and application method | |
| CN203740128U (en) | Wave-rider aircraft | |
| CN106314802A (en) | Parachute bay device for unmanned aerial vehicle and unmanned aerial vehicle | |
| US2981499A (en) | Aircraft with auxiliary launching aircraft | |
| US4589615A (en) | Store load and ejector device for aircraft | |
| CN108482679A (en) | Towed bird system that is a kind of while lifting two frame unmanned planes | |
| CN208053673U (en) | A kind of unmanned plane is fixed with booster rocket and is oriented to separating mechanism | |
| CN109515732B (en) | Combined aircraft based on barrel type launching | |
| CN215514145U (en) | Unmanned aerial vehicle stores pylon that can carry and release ammunition | |
| CN106218913B (en) | Turbine ejector | |
| DE10338963A1 (en) | Launching cruise missiles under extractable transport aircraft platforms by airdrop involves supplying energy/initialization/release-interaction data from weapon control mission planning container | |
| US2277242A (en) | Airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 17905720 Country of ref document: EP Kind code of ref document: A1 |
|
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| 32PN | Ep: public notification in the ep bulletin as address of the adressee cannot be established |
Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205A DATED 20.02.2020) |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 17905720 Country of ref document: EP Kind code of ref document: A1 |