WO2010138033A1 - Load bearing assembly for an uav-helicopter - Google Patents

Load bearing assembly for an uav-helicopter Download PDF

Info

Publication number
WO2010138033A1
WO2010138033A1 PCT/SE2009/050602 SE2009050602W WO2010138033A1 WO 2010138033 A1 WO2010138033 A1 WO 2010138033A1 SE 2009050602 W SE2009050602 W SE 2009050602W WO 2010138033 A1 WO2010138033 A1 WO 2010138033A1
Authority
WO
WIPO (PCT)
Prior art keywords
uav
helicopter
carrier
bearing assembly
load bearing
Prior art date
Application number
PCT/SE2009/050602
Other languages
French (fr)
Inventor
Per-Erik Cardell
Kjell Stenbom
Original Assignee
Saab Ab
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Saab Ab filed Critical Saab Ab
Priority to PCT/SE2009/050602 priority Critical patent/WO2010138033A1/en
Publication of WO2010138033A1 publication Critical patent/WO2010138033A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C17/00—Aircraft stabilisation not otherwise provided for
    • B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/17—Helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
    • B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • B64U2101/31—UAVs specially adapted for particular uses or applications for imaging, photography or videography for surveillance

Definitions

  • the present invention relates to a load bearing assembly in accordance with the pre- amble of claim 1.
  • the present invention also relates to an UAV-helicopter in accordance with claim 9.
  • Unmanned helicopters so called UAV-helicopters (UAV, Unmanned Aerial Vehicle)
  • UAV-helicopters UAV, Unmanned Aerial Vehicle
  • the UAV-helicopter is equipped with a payload suited for the relevant application, such as a camera or a radar unit.
  • UAV-helicopters are small sized and light-weight in comparison with standard helicopters. Consequently, the weight of the pay-load easily affects the centre of gravity of the UAV-helicopter, which should coincide with the axis of rotation of the main rotor.
  • An unbalanced UAV-helicopter e.g. where the centre of gravity does not coincide with the centre of rotation of the main rotor may therefore jeopardize the flying ability of the UAV-helicopter.
  • different payloads may vary in appearance, shape and weight. Thus, it may be difficult to properly pack the pay-load in the UAV-helicopter while maintaining the desired centre of gravity.
  • a solution to this centre of gravity problem is to use lead weights arranged on different locations in the helicopter so as to compensate for any unfavourable centre of gravity eccentricities or displacements. However, such a measure adds unnecessary weight to the UAV-helicopter.
  • the objective problem to be solved by the present invention is to maintain a stable flying ability of the UAV-helicopter when using different types of pay-loads. Yet an objective problem is to avoid the use of lead weights as a means for compensating for centre of gravity eccentricities.
  • Another objective problem is to reduce the fuel consumption of the UAV-helicopter.
  • the position of the carrier is continuously adjustable in the longitudinal di- rection of the UAV-helicopter.
  • an accurate positioning of the carrier and the pay-load and thereby an accurate adjustment of the centre of gravity of the UAV- helicopter can be achieved.
  • the carrier is arranged externally of the UAV-helicopter, and pref- erably the carrier is arranged underneath the UAV-helicopter.
  • the carrier is achieved an excellent position for surveillance purposes, such as by means of the camera or the radar unit.
  • the external position also facilitates mounting and adjustment work.
  • the UAV-helicopter also comprises a guiding arrangement for guiding the carrier in the longitudinal direction of the UAV-helicopter.
  • the guiding arrangement is provided in a frame section of the UAV-helicopter and comprises at least one longitudinal groove as well as connection means for connection to the carrier and mating with the groove, so as to allow said carrier to slide within the groove, and preferably the groove is substantially T- shaped and the connection means comprises at least one screw-nut joint mating with the T-shaped groove.
  • the guiding arrangement is provided in a frame section of the UAV-helicopter and comprises at least one longitudinal groove as well as connection means for connection to the carrier and mating with the groove, so as to allow said carrier to slide within the groove, and preferably the groove is substantially T- shaped and the connection means comprises at least one screw-nut joint mating with the T-shaped groove.
  • the groove has been milled-out from a bottom portion of the frame section.
  • the groove has been milled-out from a bottom portion of the frame section.
  • Fig. 1 shows a view seen from below of an UAV-helicopter according to the present invention
  • Fig. 2 shows a close up view of the encircled area in fig. 1
  • Fig. 3 shows an exploded view of a camera unit fitted to a carrier according to the present invention.
  • Fig. 1 shows a view seen from below of an UAV-helicopter 1 according to the pre- sent invention.
  • the UAV-helicopter comprises a frame work 3 (partly shown) covered by a fuselage 5.
  • a load bearing assembly 7 of the UAV-helicopter is provided for carrying a pay-load 9, such as a camera or a radar unit.
  • Fig. 2 is an enlarged view of the encircled area in fig. 1 and shows the load bearing assembly 7 of the UAV-helicopter.
  • This load bearing assembly comprises a carrier 11 and a guiding arrangement 13 for guiding the carrier in the longitudinal direction of the UAV-helicopter, so as change the position of the carrier 11 with respect to the guiding arrangement 13.
  • the guiding arrangement is comprised of two parallel grooves 13', 13", which each extends in the longitudinal direction of the UAV- helicopter. The grooves have been milled-out from a bottom portion of the frame section 3.
  • the carrier comprises a plate element 11 and functions as a sleigh, which can slide in the grooves of the guiding arrangement 13 by means of connection means (see fig. 3).
  • a camera 9 is in this embodiment attached to the carrier 11, but it is conceivable to attach other electronic devices such as a radar unit.
  • each groove 13 has a substantially T-shaped section.
  • the plate element 11 of the car- rier is provided with four countersunk through holes 17.
  • the camera 9 comprises a fastening portion 19 provided with four threaded holes 21 at the same locations as the through holes 17 of the plate element. Consequently, by means of screws 23 and spacers 25 the camera 9 can be securely attached to the plate element 11 at a distance determined by the size of the spacers.
  • the plate element 11 is also provided with connection means for connecting the plate element 11 to the guiding arrangement 13 and comprises two sets of two through holes 27', 27", screws 29 and sliding nuts 31.
  • Each through hole is located in a corner of the plate element 11 , and the distance between the two sets of through holes corresponds to the distance between the parallel grooves 13', 13" of the guiding arrangement.
  • These through holes serve, together with the screws 29 and the sliding nuts 31, to connect the carrier 11, to the guiding arrangement 13.
  • Each nut 31 is rectangular in shape and is sized so that they can be securely fitted in the respective T-shaped grooves 13', 13". Consequently, the carrier 11 can be suspended from the guiding arrangement 13 by means of the nuts 31. In this position, the carrier 11 can slide along the grooves 13', 13", i.e.
  • the screws 29 can be tightened so as to securely lock the carrier 11 at the desired location. In this position, the centre of gravity should coincide with the rotation axis of the main rotor.

Abstract

The present invention relates to a load bearing assembly (7) for an UAV-helicopter (1) and which comprises a carrier (11) for a payload, such as a camera or a radar unit, wherein the carrier (11) is movable and lockable in the longitudinal direction of the UAV-helicopter, so as to adjust the centre of gravity of the UAV-helicopter (1). The present invention also relates to an UAV-helicopter being provided with such a load bearing assembly.

Description

Load bearing assembly for an UAV-helicopter
TECHNICAL FIELD
The present invention relates to a load bearing assembly in accordance with the pre- amble of claim 1.
The present invention also relates to an UAV-helicopter in accordance with claim 9.
BACKGROUND OF THE INVENTION Unmanned helicopters, so called UAV-helicopters (UAV, Unmanned Aerial Vehicle), can be employed for surveillance purposes in a variety of applications. To this end, the UAV-helicopter is equipped with a payload suited for the relevant application, such as a camera or a radar unit.
However, UAV-helicopters are small sized and light-weight in comparison with standard helicopters. Consequently, the weight of the pay-load easily affects the centre of gravity of the UAV-helicopter, which should coincide with the axis of rotation of the main rotor. An unbalanced UAV-helicopter, e.g. where the centre of gravity does not coincide with the centre of rotation of the main rotor may therefore jeopardize the flying ability of the UAV-helicopter. However, different payloads may vary in appearance, shape and weight. Thus, it may be difficult to properly pack the pay-load in the UAV-helicopter while maintaining the desired centre of gravity. A solution to this centre of gravity problem is to use lead weights arranged on different locations in the helicopter so as to compensate for any unfavourable centre of gravity eccentricities or displacements. However, such a measure adds unnecessary weight to the UAV-helicopter.
OBJECTS OF THE INVENTION
The objective problem to be solved by the present invention is to maintain a stable flying ability of the UAV-helicopter when using different types of pay-loads. Yet an objective problem is to avoid the use of lead weights as a means for compensating for centre of gravity eccentricities.
Another objective problem is to reduce the fuel consumption of the UAV-helicopter.
SUMMARY OF THE INVENTION
These problems have been solved by means of a load bearing assembly as initially defined and having features according to the characterising portion of claim 1. The problems are also solved by means of an UAV-helicopter as defined in claim 9. Since the carrier is movable and lockable in the longitudinal direction of the UAV- helicopter, the centre of gravity of the UAV-helicopter can be adjusted so it coincides with the axis of rotation of the main rotor. Accordingly, a more stable flying ability can be achieved. Moreover, lead weights are not required to compensate for any centre of gravity eccentricities due to the weight influence of the pay-load. Since the lead weights become superfluous the UAV-helicopter does not have to carry redundant weight whereby the fuel consumption of the UAV-helicopter can be reduced.
Suitably, the position of the carrier is continuously adjustable in the longitudinal di- rection of the UAV-helicopter. Thus, an accurate positioning of the carrier and the pay-load and thereby an accurate adjustment of the centre of gravity of the UAV- helicopter can be achieved.
Advantageously, the carrier is arranged externally of the UAV-helicopter, and pref- erably the carrier is arranged underneath the UAV-helicopter. Hereby is achieved an excellent position for surveillance purposes, such as by means of the camera or the radar unit. The external position also facilitates mounting and adjustment work.
Suitably, the UAV-helicopter also comprises a guiding arrangement for guiding the carrier in the longitudinal direction of the UAV-helicopter. Hereby is achieved a way of reliably securing a correct positioning of the carrier. Advantageously, the guiding arrangement is provided in a frame section of the UAV-helicopter and comprises at least one longitudinal groove as well as connection means for connection to the carrier and mating with the groove, so as to allow said carrier to slide within the groove, and preferably the groove is substantially T- shaped and the connection means comprises at least one screw-nut joint mating with the T-shaped groove. Hereby is achieved a simple way of moving, adjusting and locking said carrier in the longitudinal direction of the UAV-helicopter.
Preferably, the groove has been milled-out from a bottom portion of the frame section. Hereby is achieved a simple way of providing the guiding arrangement in the UAV-helicopter.
BRIEF DESCRIPTION OF THE DRAWINGS The invention will now be described with reference to accompanying drawings, on which:
Fig. 1 shows a view seen from below of an UAV-helicopter according to the present invention,
Fig. 2 shows a close up view of the encircled area in fig. 1 , Fig. 3 shows an exploded view of a camera unit fitted to a carrier according to the present invention.
DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS Fig. 1 shows a view seen from below of an UAV-helicopter 1 according to the pre- sent invention. Several parts of the UAV-helicopter have been removed for clarity reasons, such as landing gear and rotors. The UAV-helicopter comprises a frame work 3 (partly shown) covered by a fuselage 5. At an underside of the framework 3 a load bearing assembly 7 of the UAV-helicopter is provided for carrying a pay-load 9, such as a camera or a radar unit. Fig. 2 is an enlarged view of the encircled area in fig. 1 and shows the load bearing assembly 7 of the UAV-helicopter. This load bearing assembly comprises a carrier 11 and a guiding arrangement 13 for guiding the carrier in the longitudinal direction of the UAV-helicopter, so as change the position of the carrier 11 with respect to the guiding arrangement 13. The guiding arrangement is comprised of two parallel grooves 13', 13", which each extends in the longitudinal direction of the UAV- helicopter. The grooves have been milled-out from a bottom portion of the frame section 3. The carrier comprises a plate element 11 and functions as a sleigh, which can slide in the grooves of the guiding arrangement 13 by means of connection means (see fig. 3). A camera 9 is in this embodiment attached to the carrier 11, but it is conceivable to attach other electronic devices such as a radar unit. As also depicted in fig. 2, each groove 13 has a substantially T-shaped section.
In fig. 3 the carrier 11 and the camera 9 are shown. The plate element 11 of the car- rier is provided with four countersunk through holes 17. The camera 9 comprises a fastening portion 19 provided with four threaded holes 21 at the same locations as the through holes 17 of the plate element. Consequently, by means of screws 23 and spacers 25 the camera 9 can be securely attached to the plate element 11 at a distance determined by the size of the spacers.
The plate element 11 is also provided with connection means for connecting the plate element 11 to the guiding arrangement 13 and comprises two sets of two through holes 27', 27", screws 29 and sliding nuts 31. Each through hole is located in a corner of the plate element 11 , and the distance between the two sets of through holes corresponds to the distance between the parallel grooves 13', 13" of the guiding arrangement. These through holes serve, together with the screws 29 and the sliding nuts 31, to connect the carrier 11, to the guiding arrangement 13. Each nut 31 is rectangular in shape and is sized so that they can be securely fitted in the respective T-shaped grooves 13', 13". Consequently, the carrier 11 can be suspended from the guiding arrangement 13 by means of the nuts 31. In this position, the carrier 11 can slide along the grooves 13', 13", i.e. in the longitudinal direction of the UAV-helicopter for adjusting the position of the carrier 11 with respect to the grooves 13, 13" and thereby adjust the centre of gravity of the UAV-helicopter 1. Finally, when a desired centre of gravity adjustment has been attained, the screws 29 can be tightened so as to securely lock the carrier 11 at the desired location. In this position, the centre of gravity should coincide with the rotation axis of the main rotor.
It is conceivable to provide carriers having plate elements of different geometries and dimensions so as to fit to payloads of different dimensions.

Claims

1. Load bearing assembly (7) for an UAV-helicopter (1), comprising a carrier (11) for a payload, such as a camera or a radar unit, characterised in that the carrier (11) is movable and lockable in the longitudinal direction of the UAV-helicopter (1).
2. Load bearing assembly according to claim 1, wherein the position of the carrier (11) is continuously adjustable in the longitudinal direction of the UAV- helicopter.
3. Load bearing assembly according to any of claim 1 or 2, wherein the carrier (11) is arranged externally of the UAV-helicopter.
4. Load bearing assembly according to any of the previous claims, wherein the carrier (11) is arranged underneath the UAV-helicopter.
5. Load bearing assembly according to any of the previous claims, further comprising a guiding arrangement (13) for guiding the carrier (11) in the longitudinal direction of the UAV-helicopter.
6. Load bearing assembly according to claim 5, wherein the guiding arrangement (13) is provided in a frame section (3) of the UAV-helicopter and comprises at least one longitudinal groove (13', 13") as well as connection means (27, 29, 31) for connection to the carrier (11) and mating with the groove (13', 13"), so as to allow said carrier (11) to slide within the groove
(13', 13").
7. Load bearing assembly according to claim 6, wherein the groove (13', 13") has been milled-out from a bottom portion of the frame section (3).
8. Load bearing assembly according to any of claim 6-7, wherein the groove (13', 13") is substantially T-shaped and the connection means (27, 29, 31) comprises a screw-nut joint mating with the T-shaped groove.
9. UAV-helicopter (1) comprising a load bearing assembly (7) according to any of claims 1-8.
PCT/SE2009/050602 2009-05-26 2009-05-26 Load bearing assembly for an uav-helicopter WO2010138033A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/SE2009/050602 WO2010138033A1 (en) 2009-05-26 2009-05-26 Load bearing assembly for an uav-helicopter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2009/050602 WO2010138033A1 (en) 2009-05-26 2009-05-26 Load bearing assembly for an uav-helicopter

Publications (1)

Publication Number Publication Date
WO2010138033A1 true WO2010138033A1 (en) 2010-12-02

Family

ID=43222919

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2009/050602 WO2010138033A1 (en) 2009-05-26 2009-05-26 Load bearing assembly for an uav-helicopter

Country Status (1)

Country Link
WO (1) WO2010138033A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1583010A1 (en) * 2003-11-05 2005-10-05 Deutsche Börse Ag System and method for controlling resource group transfers
CN106428598A (en) * 2016-12-21 2017-02-22 陈翔斌 Unmanned aerial vehicle and pan-tilt thereof
WO2017041466A1 (en) * 2015-09-11 2017-03-16 深圳市大疆创新科技有限公司 Shooting device and unmanned aerial vehicle
US11753146B1 (en) * 2018-07-09 2023-09-12 Pinto Geoffrey P VTOL aircraft having modular payload

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404195A (en) * 1943-06-29 1946-07-16 York Res Corp Cargo aircraft
US2684218A (en) * 1948-04-15 1954-07-20 Fairchild Engine & Airplane Aircraft cargo handling system
US4138078A (en) * 1977-05-31 1979-02-06 Textron Inc. Helicopter cargo hook apparatus
US4188000A (en) * 1977-07-26 1980-02-12 Dalziel David G Air rescue net
JPH0717491A (en) * 1993-07-06 1995-01-20 Mitsubishi Heavy Ind Ltd Center of gravity movable type helicopter
US20030222177A1 (en) * 2002-05-28 2003-12-04 Bonisch Frank H. Modular integrated self-contained cargo deployment/retrieval system
US6666404B1 (en) * 2002-10-08 2003-12-23 The Boeing Company Tripodal modular unmanned rotorcraft
US20060038077A1 (en) * 2004-06-10 2006-02-23 Goodrich Corporation Aircraft cargo locating system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404195A (en) * 1943-06-29 1946-07-16 York Res Corp Cargo aircraft
US2684218A (en) * 1948-04-15 1954-07-20 Fairchild Engine & Airplane Aircraft cargo handling system
US4138078A (en) * 1977-05-31 1979-02-06 Textron Inc. Helicopter cargo hook apparatus
US4188000A (en) * 1977-07-26 1980-02-12 Dalziel David G Air rescue net
JPH0717491A (en) * 1993-07-06 1995-01-20 Mitsubishi Heavy Ind Ltd Center of gravity movable type helicopter
US20030222177A1 (en) * 2002-05-28 2003-12-04 Bonisch Frank H. Modular integrated self-contained cargo deployment/retrieval system
US6666404B1 (en) * 2002-10-08 2003-12-23 The Boeing Company Tripodal modular unmanned rotorcraft
US20060038077A1 (en) * 2004-06-10 2006-02-23 Goodrich Corporation Aircraft cargo locating system

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1583010A1 (en) * 2003-11-05 2005-10-05 Deutsche Börse Ag System and method for controlling resource group transfers
WO2017041466A1 (en) * 2015-09-11 2017-03-16 深圳市大疆创新科技有限公司 Shooting device and unmanned aerial vehicle
US10766635B2 (en) 2015-09-11 2020-09-08 Sz Dji Osmo Technology Co., Ltd. Stabilizing platform
CN106428598A (en) * 2016-12-21 2017-02-22 陈翔斌 Unmanned aerial vehicle and pan-tilt thereof
WO2018113519A1 (en) * 2016-12-21 2018-06-28 陈翔斌 Pan-tilt for unmanned aerial vehicle, and unmanned aerial vehicle
CN106428598B (en) * 2016-12-21 2019-05-10 深圳市旗客智能技术有限公司 A kind of unmanned machine head and unmanned plane
US11753146B1 (en) * 2018-07-09 2023-09-12 Pinto Geoffrey P VTOL aircraft having modular payload

Similar Documents

Publication Publication Date Title
US10099783B1 (en) Accessory mounting for rotary wing aircraft
US10640193B2 (en) Mounting systems for mounting an element to a surface
US8251308B2 (en) Bottom blade type trefoil flight vehicle
WO2010138033A1 (en) Load bearing assembly for an uav-helicopter
EP1596075B1 (en) Three-dimensionally adjustable mounting device
CN110282144B (en) Shock-absorbing structure and use this shock-absorbing structure's cloud platform subassembly, unmanned aerial vehicle
US20130206914A1 (en) Sensor Pod Mount for an Aircraft
CN104265829A (en) Integrated absorber having hinge and vibration isolation functions and initiative and passive vibration isolation system
EP3011634B1 (en) Universal adapter plate assembly
WO2021134584A1 (en) Motion sensor module and movable platform
CN113184204B (en) Unmanned aerial vehicle's damping cloud platform and unmanned aerial vehicle
CN211685663U (en) Three-axis nacelle
EP3476714B1 (en) Mechanisms, systems and methods to allow step-adjustment of aerodynamic surfaces
CN111348208A (en) Anti-sweeping stable integrated multi-ring frame platform for airborne wide-area reconnaissance and monitoring application
CN102853221B (en) Quickly-assembled/disassembled inner-frame mechanism of airborne photoelectric platform
CN207595277U (en) A kind of preposition single arm type gondola hanger
CN100554835C (en) Cooling device
CN206615388U (en) One kind is used for unmanned plane automatic balancing bracket
KR20190118842A (en) Mission Payload Incorporating Module having C.G Adjustment Device for Unmanned Aerial Vehicle
CN209745476U (en) Be applicable to unmanned aerial vehicle focus measuring device
CN108016635B (en) Flexible overlapped satellite balancing weight
CN104669161B (en) Localizer micromatic setting
CN210101983U (en) Six rotor unmanned aerial vehicle
CN207860461U (en) Unmanned aerial vehicle group attachment device and unmanned aerial vehicle group loading system
CN108459624B (en) Self-adaptive stabilizing device for photoelectric tracker rotating at small angle

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: 09845308

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 09845308

Country of ref document: EP

Kind code of ref document: A1